STTR Phase I Solicitation   Abstract Archives

NASA SBIR 2020-I Solicitation


PROPOSAL NUMBER:
 20-1- A1.02-5030
SUBTOPIC TITLE:
 Quiet Performance - Aircraft Propulsion Noise
PROPOSAL TITLE:
 A Computational Tool for Fan Broadband Noise Prediction
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
D&P, LLC
3409 North 42nd Place
Phoenix, AZ 85018
(480) 518-0981

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Lei Tang
E-mail:
tanglei@d-p-llc.com
Address:
3409 North 42nd Place Phoenix, AZ 85018 - 5961
Phone:
(480) 518-0981

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Lei Tang
E-mail:
tanglei@d-p-llc.com
Address:
3409 North 42nd Place Phoenix, AZ 85018 - 5961
Phone:
(480) 518-0981
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

This SBIR project proposes to develop a computational tool for fan broadband noise prediction based on a large-eddy-simulation (LES) approach. The proposed approach combines the advantages of those existing high-fidelity methods in literature for simulation of NASA 22-in fan noise source diagnostic test (SDT), i.e., the LES with the WALE SGS model for turbulence simulation and modeling, and the Cartesian mesh approach for rotor-stator coupling, and the consideration of the whole rotor and stator annulus in simulation. Much more accurate spatial discretization schemes will also be used for improving the prediction of turbulent eddies and acoustic waves. As a feasibility study, the Phase I outcome will demonstrate the feasibility of the proposed LES approach for accurate simulation of NASA 22-in fan noise source diagnostic test. Therefore, it is meaningful to fully develop, demonstrate, and validate this software tool in Phase II.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The Advanced Air Transport Technology (AATT) and Commercial Supersonic Technology (CST) Projects would benefit from the developed computational tool that could be used to predict the performance and noise impacts of those novel engine installations for noise reduction. The Transformational Tools and Technologies (TTT) Project would benefit from the developed computational tool to enhance the ability to consider acoustics earlier in the aircraft design process.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

DoD's High Performance Computing Modernization Program would benefit from this computational tool that could provide them a useful tool for fan broadband noise prediction. Design engineers in engine manufacturers can use the developed computational tool to explore various noise reduction concepts and validate fast, low-fidelity analytical methods for trade-off studies and performance prediction.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z5.04-5732
SUBTOPIC TITLE:
 Technologies for Intra-Vehicular Activity Robotics
PROPOSAL TITLE:
 Magnetic Interfaces for IVR Logistics, Cargo Management and Outfitting
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Altius Space Machines, Inc.
3001 Industrial Lane, Unit #5
Broomfield, CO 80020
(801) 362-2310

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Michael Bowker
E-mail:
mbowker@altius-space.com
Address:
3001 Industrial Lane Broomfield, CO 80020 - 7153
Phone:
(281) 330-2324

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Jonathan Goff
E-mail:
jongoff@altius-space.com
Address:
3001 Industrial Lane, Unit #5 Broomfield, CO 80020 - 7153
Phone:
(801) 362-2310
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

For deep-space habitats, especially ones left in orbit around a destination planet or Moon, astronaut time at the habitat will be both infrequent and very valuable and it would be extremely desirable for robots to outfit the habitat prior and to allow robots to perform maintenance and logistics tasks. While theoretically it may be possible to design robots to interact with a habitat designed without robotic interactions in mind, the addition of cooperative robotic interaction features can dramatically simplify and improve the robustness of the robotic outfitting hardware. These robotic interaction aids ideally can serve three purposes: 1) helping robots determine their relative pose and position with respect to the target, and their relative location/pose inside or outside the habitat, 2) identifying what the objects are, especially if the objects are mobile like soft-goods bags, and 3) simplifying physical interactions with the object, including anchoring to and manipulating the object. To enable these types of robotic interactions, Altius proposes leveraging our existing commercially available (TRL8/9) “DogTag” grapple fixture and developing a lightweight, low-cost, passive robotic magnetic interface (IVR DogTags) that can be attached to various habitat structures and objects. We envision using our patented electropermanent magnet (EPM) based gripper for interfacing with the IVR DogTags. The IVR  interface includes: 1) a thin ferromagnetic material layer that allows robots to magnetically grip the DogTag, 2) a long-range optical fiducial printed and attached to the DogTag’s surface that allows the robot to determine relative pose and position of the object & 3)methods for attaching the DogTag to the desired object including rigid surfaces and soft-goods objects. The other half of the interface is the EPM gripper, which uses an electrically switched permanent magnet with no moving parts to enable secure attachment to and release from the IVR DogTag interfaces.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed solution provides an active electropermanent magnet (EPM) based gripper head integrated with the Astrobee and a passive robotic magnetic interface (IVR DogTags) that can be attached to various habitat structures and objects to perform IVR logistics, cargo management and outfitting activities.  This solution is applicable to ISS, Gateway and other facilities that benefit from robotic maintenance of habitat sub-assemblies for long duration missions.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed solution provides  supports various habitat structures and objects to perform IVR logistics, cargo management and outfitting activities.  This solution is applicable to commercial facilities  (Axiom/Nanoracks) that would benefit from robotic maintenance of habitat sub-assemblies for long duration missions.

Duration: 6

PROPOSAL NUMBER:
 20-1- A1.01-6125
SUBTOPIC TITLE:
 Aeroelasticity and Aeroservoelastic Control
PROPOSAL TITLE:
 Decomposed Reduced-Order Modeling for Flutter and LCO Predictions in Highly Nonlinear Systems
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Corvid Technologies
153 Langtree Campus Drive
Mooresville, NC 28117
(704) 799-6944

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Greg McGowan
E-mail:
greg.mcgowan@corvidtec.com
Address:
145 Overhill Drive Mooresville, NC 28117 - 8006
Phone:
(704) 799-6944

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Tracy Williams
E-mail:
tracy.williams@corvidtec.com
Address:
145 Overhill Drive Mooresville, NC 28117 - 8006
Phone:
(405) 410-6552
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Modeling aircraft aeroelastic response is an incredibly challenging process fraught with many questions regarding the approaches and assumptions in both structural and aerodynamic analyses.  Modeling 3-D, full scale, fully coupled, aerodynamic and structural responses with high-fidelity computational approaches is only viable for evaluating a few conditions within the flight envelope, but intractable for defining a flutter boundary over a range of flight speeds.  To alleviate these challenges researchers have developed reduced order models to facilitate the aerodynamic calculations at a fraction of the cost.  These methods are incredibly powerful, but present significant problems when attempting to apply in the case of highly nonlinear flows as they can be costly to maintain fidelity required in the modeled response.  These nonlinear flows play a critical role in the aeroelastic response and as such require that the reduced order models provide a high level of fidelity. 

The proposed research will demonstrate a framework that decomposes nonlinear aerodynamic responses, in the form of Generalized Aerodynamic Forces based upon dynamical models which are then extended to the nonlinear range based upon the concept of a Volterra series.  By decomposing the Volterra series into the linear and nonlinear parts a significant cost savings can be leveraged as the linear terms can remain fixed for a given choice of flow parameters and the Volterra series need only serve to reproduce the nonlinear response of the system.  By taking this approach to modeling the aerodynamics we hypothesize an improvement in the reduced order model’s ability to reproduce an accurate nonlinear representation of the aerodynamics at a greatly reduced cost.  This will aid in both increasing the fidelity of aeroelastic predictions and provide a valuable resource to utilize in the development of aeroservoelastic control logic.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Applications are far reaching as all airframes require aeroelastic evaluation in the design stages to ensure safe flight. Aircraft that operate in the high-subsonic or transonic regime where complex shock structures can develop and move rapidly over the wing surfaces are also strong candidates for this modeling approach. Aircraft with structural complexity that can introduce strong aerodynamic interactions such as engine/nacelle/pylon interference or store load out may also be viable candidates for this modeling approach.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Interest in airframes from DoD may include fighter squadrons with varying store load outs. This is a challenging problem as the store loadout and positioning can produce significant aerodynamic shock interactions and other nonlinearities. There may also be opportunities in the private aircraft industry as well for aircraft designs are pushed outside the bounds that are currently well understood.

Duration: 6

PROPOSAL NUMBER:
 20-1- S5.06-6130
SUBTOPIC TITLE:
 Space Weather R2O/O2R Technology Development
PROPOSAL TITLE:
 Time-Dependent Connectivity Mapping of the Solar Magnetic Field
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Predictive Science, Inc.
9990 Mesa Rim Road, Suite 170
San Diego, CA 92121
(858) 450-6494

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Jon Linker
E-mail:
linkerj@predsci.com
Address:
9990 Mesa Rim Road, Suite 170 San Diego, CA 92121 - 3933
Phone:
(858) 450-6494

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Meaghan Marsh
E-mail:
office@predsci.com
Address:
9990 Mesa Rim Road, Suite 170 San Diego, CA 92121 - 3933
Phone:
(858) 450-6494
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

The ambient solar magnetic field plays a key role in heliophysics in general and in space weather in particular.  It is especially important for the propagation of solar energetic particles (SEPs), guiding them along the magnetic field from their generation near the Sun to locations in the heliosphere.  Solar Particle Events (SPEs), arising from SEPs produced by solar eruptions, represent a significant hazard for humans and technological infrastructure.  Providing longer range (2-3 day) forecasts of SPEs and/or all-clear periods is highly desirable but difficult to achieve, because a forecast must occur prior to the start of the eruption.  Given a flare/CME forecast, a major source of uncertainty in SPEs is the magnetic connectivity.  The goal of  our project is to develop CORHEL-E (CORHEL with Evolution).  CORHEL-E will provide time-dependent coronal and solar wind solutions, driven by evolving boundary conditions provided by photospheric flux transport models.  In phase I of our project, we will demonstrate time-dependent estimates of magnetic connectivity of Earth for specific time periods, using ensembles of solutions to assess variability and uncertainty.  At the completion of phase II, we will provide CORHEL-E to the CCMC, capable of running continuously.  Given a flare/eruption forecast from a threatening active region, CORHEL-E will allow the user to assess the regional connectivity and likelihood that SEPs can reach Earth or other heliospheric locations of interest.  Using STAT, an eruption can actually be simulated and particle fluxes predicted.  Longer term, our vision for an operational capability is a near-real time model of the solar corona and inner heliosphere, updated with new magnetic (and other) observations as they become available.  CMEs would be initiated in the model after being observed, and then be simulated as part of the continuous solution.  The development of CORHEL-E is a crucial next step towards this goal.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

SPEs are of particular concern to NASA  SRAG,  which is responsible  for  ensuring that the radiation exposure received by astronauts remains below established safety limits.  Connectivity of the solar magnetic field plays a crucial role in determining where the particles propagate.  CORHEL-E will provide a tool for assessing this connectivity.  It complements tools presently used in operations such as MAG4, and can be used in conjunction with the SPE Threat Assessment Tool (STAT) already delivered to the CCMC at NASA GSFC.
 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

SPEs are of concern to many government and commercial entities dependent on satellites and aircraft.  For example, NOAA SWPC provides space weather information to customers requiring forecasting of SPEs.  The Air Force is also interested in mitigation strategies for SPEs.  CORHEL-E can improve longer range forecasting of SPE events/all clear forecasts for these agencies as well.

Duration: 6

PROPOSAL NUMBER:
 20-1- A3.03-5041
SUBTOPIC TITLE:
 Future Aviation Systems Safety
PROPOSAL TITLE:
 TRACAIR: TRAjectory Course Anomaly Identifier
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Global Technology Connection, Inc.
2839 Paces Ferry Road, Suite 1160
Atlanta, GA 30339
(770) 803-3001

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Jesse Williams
E-mail:
jwilliams@globaltechinc.com
Address:
2839 Paces Ferry Road, Suite 1160 Atlanta, 30339 - 5770
Phone:
(770) 803-3001

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ash Thakker
E-mail:
athakker@globaltechinc.com
Address:
2839 Paces Ferry Road, Suite 1160 Atlanta, GA 30339 - 5770
Phone:
(770) 803-3001
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Global Technology Connection, Inc. and its partners propose to develop a flexible state-of-the-art capability focused on identification of trajectory anomalies, based on energy metrics, using a fusion of data from multiple sources (e.g., OpenSky Network data, Traffic  Flow  Management  System  Data, Automated Surface Observing System Data) in order to identify and isolate potential causal factors and/or anomalies, and help improve safety of operations in terminal areas.

Future aviation systems such as the NextGen, and Single European Sky ATM Research (SESAR) are moving towards utilize 4D trajectory management concept in order to improve efficiency, reliability, sustainability and cost-effectiveness of aircraft operations. This will require aircraft to follow an assigned 4D-trajectory (time-constrained trajectory) with high precision. By detecting trajectory anomalies, safety-critical risks include flight outside of approved airspace, unsafe proximity to people/property, loss of command, control, power, loss or degraded GPS, and engine failure can be identified in real time to be used for prognosis and resolution of system-wide threats.

Despite numerous implementations of anomaly detection using flight data, there are limited frameworks that fused data from multiple sources (weather information, system level metrics related to congestion, traffic, etc.), which is what we are proposing by performing the following technical tasks: Identification of data sources, Data fusion, Deep autoencoder model development, Post-processing.

In phase I, we develop a prototype for proof-of-concept. In Phase II, we add other data sources and develop a commercial prototype for NASA applications and design a verification & validation process to meet the NASA requirements. In Phase III, we develop the commercial version of the software package for NASA and Non-NASA applications, and continue commercialization of the intended product.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)
  • UAS Traffic Management (UTM):
    This technology can be used to fuse different data sources to detect intentional (e.g., terrorist attack) and/or unintentional (e.g., damaged drones) anomalies in low altitude drones’ trajectories. 
  • Urban Air Mobility (UAM):
    This technology can be used in UAM project to detect anomalies in future vehicles and systems such as personal taxi service by air, air medical services, and cargo delivery to under-serviced communities that could revolutionize mobility in and around densely populated metropolitan areas.
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)
  • Predicting safety of the current (Boeing, Airbus, Lockheed martin etc.) and NextGen vehicles.
  • Integrating health monitoring of distributed ground, air, space systems.
  • Improving the ability of human/automated systems to avoid hazardous weather.
  • This product is also useful for airlines' safety departments, air traffic control, airport operators.
Duration: 6

PROPOSAL NUMBER:
 20-1- Z8.09-5723
SUBTOPIC TITLE:
 Small Launcher Lunar Transfer Stage Development
PROPOSAL TITLE:
 High Performance Pump-fed Lunar Transfer Stage for Small Launchers
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Flight Works, Inc.
17905 Sky Park Circle, Suite F
Irvine, CA 92614
(949) 387-9552

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Christopher Bostwick
E-mail:
chris.bostwick@flightworksinc.com
Address:
17905 Sky Park Circle, Suite F Irvine, CA 92614 - 6707
Phone:
(949) 387-9552

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Eric Besnard
E-mail:
eric.besnard@flightworksinc.com
Address:
17905 Sky Park Circle, Suite F Irvine, CA 92614 - 6707
Phone:
(949) 387-9552
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Flight Works is proposing to expand its micropump-fed propulsion technology to the development and demonstration of a low cost, compact, high performance lunar transfer stage designed for small launchers like Rocket Lab’s Electron and Virgin Orbit’s Launcher One. With a total wet mass around 230 kg, the transfer stage is designed to provide high-thrust, high delta-V capabilities of over 3 km/s to one or more nanosat payloads weighing more than 30 kg. It will be to propel small spacecraft (CubeSat or nanosat) from Low Earth Orbit on to Trans Lunar Injection trajectories. The system can either stay attached to the small primary payload for long term mission operations, or deploy the latter at its destined lunar orbit.

 

This proposed effort builds on the extensive propulsion technology developed at Flight Works in the area of micro-pump-fed propulsion systems, combined with space system-level know-how of its principals, to provide a stage with unique benefits. These include compact, conformal low-pressure tanks/stage minimizing range safety operations and costs; high thrust for rapid, efficient transfer (compared with electric propulsion systems which have to be launched at higher orbits to avoid low altitude drag and which can require months to reach the targeted orbit); minimized size provided by a high performance propulsion system; and attitude control system during the delta-V maneuver which can ride along for cislunar operations.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

With a stage designed to provide over 3 km/s delta-V to a nanosat payload, it can be used for NASA lunar and interplanetary applications. These include missions similar to the NASA Cislunar Autonomous Positioning System Technology Operations and Navigation Experiment (CAPSTONE), or follow-ons to NASA’s Mars CubeSat missions MarCO-A and -B. It can also be used for NASA LEO and GEO nanosat missions, whether launched as dedicated or as secondary payloads.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Non-NASA applications include commercial and DoD missions requiring high orbital maneuver capabilities. These include missions on small dedicated launch vehicles where additional delta-V is required, as well as space-tug applications on Falcon-9 rideshare launches. The stage can also be used for other applications such as orbital inspectors.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z8.06-6249
SUBTOPIC TITLE:
 DragSails for Spacecraft Deorbit
PROPOSAL TITLE:
 Magsails for Spacecraft Deorbit
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Pioneer Astronautics
11111 West 8th Avenue, Unit A
Lakewood, CO 80215
(303) 984-9346

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Robert Zubrin
E-mail:
zubrin@aol.com
Address:
11111 West 8th Avenue, Unit A Lakewood, CO 80215 - 5516
Phone:
(303) 984-9346

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Robert Zubrin
E-mail:
zubrin@aol.com
Address:
11111 West 8th Avenue, Unit A Lakewood, CO 80215 - 5516
Phone:
(303) 984-9346
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

The magnetic sail, or magsail, is a new technology that can be used for deorbiting spacecraft. In the magsail deorbiting system, a loop of aluminum or copper wire is deployed at the end of life of an Earth orbiting spacecraft, and energized with an electric current, producing a magnetic field. The magnetic field forces the wire into a circular loop, and creates a small magnetosphere around the spacecraft. This magnetosphere in tern then creates drag against the ambient plasma surrounding the Earth, causing the spacecraft to deorbit. For typical configurations, the magsail wire mass required to create a drag area of a given size is two orders of magnitude less than that needed using solar sail or any other physical material. In addition to being a uniquely advantageous technology for LEO spacecraft deorbiting, the normal-conducting magsail can serve as a precursor technology to superconducting magsails capable of generating sufficient field to effectively propel interplanetary spacecraft using the momentum flux of the solar wind. In the proposed program, the potential performance of the magsail deorbiting system will be analyzed, design options compared, deployment and operation simulated, and the concept validated by means of computer analysis and laboratory tests. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Magsails using normal conductors can lower spacecraft orbits around Earth, Venus, Mars, Jupiter, Saturn, Titan, Uranus or Neptune  Magsails could be used to enable reusable orbit transfer vehicles or TLI stages to return to LEO without requiring either the expenditure of propellant or aerobraking.  Advanced superconducting magsails could be used to deliver NASA space probes to interplanetary destinations, provide shielding against solar flares, or to decelerate very fast interstellar spacecraft without the expenditure of propellant.  

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Magsails using normal conductors can be used to create drag against Earth’s ionosphere, enabling the deorbiting of commercial and military satellites with a very low mass system. Magsails could be used to deorbit GTO stages or enable reusable orbit transfer vehicles to return to LEO without requiring either the expenditure of propellant or aerobraking. 

Duration: 3

PROPOSAL NUMBER:
 20-1- Z8.08-6253
SUBTOPIC TITLE:
 Technologies to Enable Cost & Schedule Reductions for Ultra-Stable Normal Incidence Mirrors for CubeSats
PROPOSAL TITLE:
 Additively Manufactured, Ultra-Stable RoboSiC Proximity Imaging CubeSat Telescope
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Goodman Technologies, LLC
9551 Giddings Avenue Northeast
Albuquerque, NM 87109
(505) 400-8169

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Bill Goodman
E-mail:
bgoodman@goodmantechnologies.com
Address:
9551 Giddings Avenue Northeast ALbuquerque, NM 87109
Phone:
(505) 400-8169

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. William Goodman
E-mail:
bgoodman@goodmantechnologies.com
Address:
9551 Giddings Ave NE ALBUQUERQUE, NM 87109 - 6412
Phone:
(505) 400-8169
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

The purpose of sub-topic Z8.08 is to demonstrate the ability to manufacture, test and control ultra-low-cost, ultra-stable telescope systems for 12U CubeSats.  Goodman Technologies (GT) offers this proposal in partnership with the Hawaiian Nanotechnology Laboratory (HNL) and the Hawaiian Space Flight Laboratory (HSFL) at the University of Hawaii at Mānoa, (UHM, a Minority Serving Institution).  Using an ultra-stable telescope that is integral to the 12U CubeSat structure will provide the requisite dimensionally stability for precision pointing of the CubeSat to perform proximity imaging of nearby spacecraft, the moon, or Mars.  We will define with our NASA customer (ARC, GSFC, JPL) a reference proximity imaging mission which takes advantage of the 20:1 telephoto ratio of the ultra-stable RoboSiC telescope.  Key parameters to be determined for the mission and an assumed camera resolution (e.g., TBD megapixel camera) are: operating range (e.g., 1-100 km) and the resolving capability  as a function of object size and distance (e.g.,  1-10 cm resolution at a distance of 1 km for an object that is 5-m in length). We will define primary and secondary mirror radius of curvature, clear aperture, surface figure, surface roughness and optical coating requirements (e.g., enhanced/protected aluminum or a proprietary Goodman developed VIS/MWIR/LWIR radiation survivable coating with 10-year mission life), diffraction limited performance out to a full field of view (FOV) of TBD degrees, and acceptable performance out to TBD degrees. Our RoboSiC technologies are “Mission Agnostic” and tunable to requirements. GT recently demonstrated 3D printed and additively manufactured  silicon carbide mirror substrates (RoboSiC) at the 25-cm scale  for a balloon experiment (BE). This would fill a Critical Technology Gap (extreme dimensional stability) for future missions such as Origins Space Telescope (OST) and Large UV/Optical/IR Surveyor  (LUVOIR).

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Using an ultra-stable telescope that is integral to the 12U CubeSat structure will provide the requisite dimensionally stability for precision pointing of the CubeSat to perform proximity imaging of nearby spacecraft, the moon, or Mars. Other missions are LUVOIR, HabEx, OST, SPIRIT, LISA , the Balloon  Experiments GHAPS and PICTURE-C , and Low-Cost Compact Reflective Telescope for NIR/SWIR Optical Communication. The project meets the needs of multiple scientists at the lead and participating centers, and NASA Priority 1-3 Technology Gaps.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Low cost, lightweight, stable structures are required for Astronomy, optical instruments for imaging, surveillance, and reconnaissance missions for police and paramilitary units, fire fighters, power and pipeline monitoring, search and rescue, atmospheric and ocean monitoring, imagery and mapping for resource management, and disaster relief and communications.

Duration: 6

PROPOSAL NUMBER:
 20-1- A1.04-6393
SUBTOPIC TITLE:
 Electrified Aircraft Propulsion
PROPOSAL TITLE:
 Multi-Megawatt Superconducting Motor for Electric Aircraft
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Princeton Satellite Systems
6 Market Street, Suite 926
Plainsboro, NJ 08536
(609) 279-9606

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Charles Swanson
E-mail:
charles.swanson@psatellite.com
Address:
6 Market Street, Suite 926 Plainsboro, NJ 08536 - 2096
Phone:
(609) 447-2390

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Michael Paluszek
E-mail:
map@psatellite.com
Address:
6 Market Street, Suite 926 Plainsboro, NJ 08536 - 2096
Phone:
(609) 275-9606
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

In this proposal we propose to evaluate the performance of a novel configuration of superconducting electric motor. The application of this motor is propelling partially- or fully-electric aircraft. The technology has the potential to quadruple the existing state of the art in aircraft motor specific power. Gains in specific power come from several aspects of the design:

The axial flux configuration is used rather than the radial flux. Low-temperature superconductor (LTS) is used for the rotor rather than permanent magnets or high-temperature superconductor. The LTS is cooled via conduction cooling rather than helium-bath cooling. An optimized Halbach winding array concentrates magnetic flux and removes the need for back iron. A relatively high rotational speed allows for direct coupling to a propeller or ducted fan. A cryogenic Litz wire stator is used to reduce dissipation and heat transfer to the rotor. A relatively high pole count for a superconducting machine allows greater efficiency at higher electrical frequency.

In Phase I we propose to evaluate the principles using multiphysics modeling. We propose to design a 100 kg, 1 MW motor and a 1000 kg, 20 MW motor. For Phase II we would build and test the three test articles relevant to the 1 MW motor. A 1 MW motor coupled to a propeller is sufficient to replace a turboprop engine in a small business or regional airline aircraft. A 20 MW motor coupled to a ducted fan is sufficient to replace a jet engine in a large passenger aircraft.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

This proposal is relevant to commercial aircraft fuel efficiency and emissions reduction, and electrification of aircraft propulsion. These are NASA technology roadmap Technology Areas (TA) of TA15.3.1, TA15.3.3, TA15.4.1, and TA15.4.2 and NASA Technology Taxonomies (TX) of TX01.3.4, TX01.3.8, TX01.3.9, and TX01.3.10.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

A 1 MW motor coupled to a propeller is sufficient to replace a turboprop engine in a small business or regional airline aircraft. Roughly 600 of these aircraft are delivered per year. A 20 MW motor coupled to a ducted fan is sufficient to replace a jet engine in a large passenger aircraft such as the Boeing 737-800. High-power electric motors will be required for the DoD’s electric battlefield.

Duration: 6

PROPOSAL NUMBER:
 20-1- A2.02-6569
SUBTOPIC TITLE:
 Unmanned Aircraft Systems (UAS) Technologies
PROPOSAL TITLE:
 Low SWAP-C Imaging Radar for Small Air Vehicle Sense and Avoid
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
KMB Telematics, Inc.
1001 19th Street North, Suite 1200
Arlington, VA 22209
(703) 783-3377

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Marco La Manna
E-mail:
marco@kmb.ac
Address:
1001 19th St N ste 1200 Arlington, VA 22209 - 1731
Phone:
(703) 783-3377

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Bryan Cattle
E-mail:
bcatt@kmb.ac
Address:
1001 19th St N ste 1200 Arlington, VA 22209 - 1731
Phone:
(703) 783-3377
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Unmanned aircraft systems (UAS) are poised to transform modern life. However, there remain barriers to increased adoption. Current autonomous systems have poor perception of the environment. At the same time, detecting and avoiding non-cooperative aircraft in all weather is a key requirement for operation in the National Airspace (NAS). To bridge this gap, KMB Telematics Inc. is proposing the development of a low size, weight, power, and cost (SWAP-C) imaging radar for UAS sense-and-avoid applications. This sensor is based on 18 months of IRAD conducted by KMB Telematics to develop imaging radar for the automotive market. Automotive radar has seen a flurry of innovation in recent years, resulting in inexpensive, high-resolution sensors. This proposed Phase I effort will focus on the technical objectives needed to show the feasibility of adapting these technologies for UAS sense-and-avoid. By meeting these objectives, this radar will be suitable for use on small commercial package delivery UAS for which there is currently no available sense-and-avoid sensor. The proposed radar will be smaller, lighter, and more inexpensive than currently available technologies. The radar will consume less power and will be designed for redundancy and fault tolerance. The goal is for the radar developed under this SBIR to (1) accelerate the Integrated Aviation Systems Program’s ongoing effort to expand NAS access to broader classes of UAS, and (2) allow commercial package delivery UAS operators to receive FAA waivers for beyond visual line of sight (BVLOS) operations. Phase I will result in simulation, analysis, and feasibility determination needed to show that the imaging radar approach is capable of being used on lightweight, power constrained UAS platforms. Phase I will also result in a design that is ready to be prototyped in Phase II. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

This sensor would allow IASP to use smaller, cheaper UAS to perform research like the development of sense and avoid algorithms, sensor fusion, pattern recognition, and decision-making algorithms. The sensor could be used in a ground-based configuration to assist AOSP’s research related to UAS path planning, ATC, and non-cooperative surveillance. In space, this radar could be used as an Entry, Descent, and Landing (EDL) sensor for terrain mapping, for spacecraft docking, and for On Orbit-Servicing, Assembly, and Manufacturing (OSAM).

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

This sensor would enable commercial package delivery UAS operators to fly beyond visual line of sight (BVLOS). This is a large, growing market. Another potential market is counter-UAS around critical infrastructure, selling to DHS, DoD, and and commercial integrators. Also interesting is commercial spaceflight, in  precision applications like asteroid mining and landing reusable launch vehicles. 

Duration: 3

PROPOSAL NUMBER:
 20-1- H3.02-4632
SUBTOPIC TITLE:
 Microbial Monitoring for Spacecraft Cabins
PROPOSAL TITLE:
 Engineered Peptoid Sensor for Microbial Monitoring in Spacecraft Cabins
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
CatalyzeH2O, LLC
249 Alexandra Loop
Elkins, AR 72727
(918) 924-1565

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ms. Shelby Foster
E-mail:
shelby@catalyzeh2o.com
Address:
249 Alexandra Loop Elkins, AR 72727 - 3707
Phone:
(918) 924-1565

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ms. Shelby Foster
E-mail:
shelby@catalyzeh2o.com
Address:
249 Alexandra Loop Elkins, AR 72727 - 3707
Phone:
(918) 924-1565
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Currently, there is a need for sensing technology that can reliably detect microbial growth at its initial stages for air, surfaces, and potable water, well before substantial microbial growth, contamination, and microbial-induced corrosion can occur.  The current approach used to determine microbial growth is through analytical microbiology, which relies on sampling from tanks and analysis of these grab samples in a high-tech laboratory with specialized equipment (e.g., polymerase chain reaction (PCR) DNA techniques).  There are several drawbacks to this current approach.  First, analysis of the dynamics of microbial growth and microbial contamination is completely lost; single grab samples over time are unlikely to show how fast the microbial growth is advancing, and if enough grab samples are taken to try to track the dynamics of microbial growth, there is then a sample number/volume challenge in being able to analyze many samples in a timely manner.  Second, an analytical instrumentation laboratory requires highly specialized and trained scientists and operators, which limits the feasibility of many operations having good access to such a laboratory.  Third, this approach is time intensive; it often takes days to weeks to obtain and analyze grab samples in an analytical laboratory.  Finally, this approach does not offer any real-time or online information about microbial growth and therefore is likely to miss early-stage growth where identification and mitigation are ideal; the longer the microbes are allowed to grow, the worse the damage is to the air, surface, and water quality.  For all of these reasons, on-line, inline technology is desired and required to enable spacecraft operations to easily identify microbial contamination in air, surfaces, and potable water early enough to address safety and health quality concerns.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Microbial and fungal contamination of the air, surfaces, and water resources on spacecraft is a major health hazard for astronauts. The risks include infection and illness, the release of microbially-produced toxins, alteration of astronaut immune systems, and the degradation of materials and equipment on spacecraft. Therefore, the real-time monitoring of microbial growth for air, surface, and water environments for crewed and uncrewed operations would provide ample warning for microbial growth prevention methods to be implemented.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The simplicity and elegance of this approach are that the array can be used for any mixture of metabolites across gas and liquid phase because it does not rely on one-to-one binding. This allows the technology to be easily implemented into different microbiological testing markets such as the agricultural industry, the water industry, the healthcare industry, and the oil and gas industry.

Duration: 6

PROPOSAL NUMBER:
 20-1- A2.01-5620
SUBTOPIC TITLE:
 Flight Test and Measurement Technologies
PROPOSAL TITLE:
 Low-Power Backscatter Networking With Device Synchronization and Timestamping
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Jeeva Wireless Incorporated
4000 Mason Road, Suite 300
Seattle, WA 98195
(206) 478-3572

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Aaron Parks
E-mail:
aaron.parks@jeevawireless.com
Address:
4000 Mason Rd Ste 300 Seattle, WA 98195 - 0001
Phone:
(206) 478-3572

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Aaron Parks
E-mail:
aaron.parks@jeevawireless.com
Address:
4000 Mason Rd Ste 300 Seattle, WA 98195 - 0001
Phone:
(206) 478-3572
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

In the proposed R&D, Jeeva will design, implement, and characterize a protocol extension for an ultra low power backscatter networking platform which makes possible microsecond-scale time synchronization between ultra low-power sensor nodes and a wireless hub/aggregator. This will allow the unique benefits of backscatter networking to be applied in instrumentation systems for flight test and other telemetry applications, where time synchronization is a prerequisite.

Wireless instrumentation for flight testing and telemetry is viewed by ARMD as a known technology gap, and a technical challenge in IASP and FDC projects. However, implementation of conventional wireless sensing introduces concerns around battery life, weight, and volume, as well as mismatches between wireless protocol features and instrumentation system requirements.

Backscatter networking technology enables wireless data transfer at 2-3 orders of magnitude lower power than conventional radios, making it the lowest power radio link available. This translates to longer battery life in typical wireless sensor nodes, where most of the battery capacity is expended in operating the wireless link. Backscatter holds promise to substantially reduce the need to replace batteries, and/or reduce the weight/volume of batteries. However, this emerging technology doesn't yet include a means of over-the-air time synchronization, which is needed in instrumentation and telemetry applications where measurements must be taken synchronously or time-stamped.

Upon completing this project, Jeeva will have extended the backscatter networking protocol to enable wireless time synchronization between sensor node and hub, allowing synchronous data captures and time-stamping of data. A testbed will have been developed for characterization of system performance. This project will bring backscatter technology closer to readiness for applications in wireless flight test instrumentation and other wireless avionics applications.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

  • Wireless flight test instrumentation with long battery life requirements or weight/volume requirements
  • Wireless sensing for ground based test platforms with a need to simplify experimental setup procedures
  • Modularized test platforms and vehicle subsystems
  • Flight control systems requiring synchronous sampling or timestamped data
  • General wireless avionics systems
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)
  • Commercial aircraft and other private sector flight test and avionics systems
  • Telemetry applications in the railway, shipbuilding, and automotive industries
  • Time-stamped wireless microphone data streaming for acoustic localization of sound sources
  • Wireless EEG, EKG, implantable systems, and other patient monitoring systems which benefit from synchronous sampling
Duration: 4

PROPOSAL NUMBER:
 20-1- S1.10-6185
SUBTOPIC TITLE:
 Atomic Interferometry
PROPOSAL TITLE:
 High-Power Tunable 852nm Laser Source and PICs for Atom Interferometry Based Gravimetry
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Freedom Photonics, LLC
41 Aero Camino
Santa Barbara, CA 93117
(805) 967-4900

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Gordon Morrison
E-mail:
gordon@freedomphotonics.com
Address:
41 Aero Camino Goleta, CA 93117 - 9311
Phone:
(805) 967-4900

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Milan Mashanovitch
E-mail:
mashan@freedomphotonics.com
Address:
41 Aero Camino Santa Barbara, CA 93117 - 3104
Phone:
(805) 967-4900
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

In this program, Freedom Photonics is proposing to develop a low SWaP, high-power fast-tunable semiconductor laser source operating at 852 nm, critically needed for deployment of practical atomic interferometry gravimeters being developed by NASA GSFC. In addition, we will explore possibilities to further reduce the complexity, size, weight and power of the entire laser system through photonic integration of other functions to the laser

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Atomic interference gravimetry, atomic clocks

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Atomic clocks, fiber laser pumping

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.06-6213
SUBTOPIC TITLE:
 Particles and Fields Sensors & Instrument Enabling Technologies
PROPOSAL TITLE:
 Radiation-Resistant High-Resolution Particle Sensors from Composites of Semiconductor Nanoparticles and Aramid Nanofibers
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Amphionic, LLC
875 North Lima Center Road
Dexter, MI 48130
(734) 660-9412

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Suneel Joglekar
E-mail:
suneel@amphionic.com
Address:
875 North Lima Center Road Dexter, MI 48130 - 9769
Phone:
(765) 609-1308

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mark Hammig
E-mail:
hammig@yahoo.com
Address:
875 N. Lima Center Road Dexter, MI 48130 - 9769
Phone:
(734) 660-9412
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

This SBIR Phase I project will demonstrate that high radiation-resistance can be elicited from nanostructured media comprised of semiconducting nanoparticles derived from size-governed wide band-gap CdTe or PbTe. In order to transform space-based particle sensors, nanocrystalline semiconductors provide an attractive material basis because they present a means of: 1) decreasing the underlying material cost by utilizing a solution-based fabrication methodology, 2) increasing the range of candidate materials by including the narrow-gap semiconductors, 3) increasing the exciton multiplicity upon the impingement of radiation by utilizing multi-exciton generation, and 4) increasing the radiation resistance because the introduction of a high density of nanoparticles can convey pronounced improvement in the radiation hardness of the material. In order to realize these properties, several experimental challenges must be overcome, the surmounting of which is one of the objects of the proposed research, during which we will: 1) utilize self-assembly to realize close-packed quantum-dot domains where the charge transport is optimized, and 2) extend the size of those domains to macroscopic size.  The research is designed to not only deliver a high-performance radiation resistant sensor that can be commercialized but it will also advance basic physics by studying the interactions between energetic particles and strongly-confined charge carriers. By finding general material-design methods to suppress both radiation-induced damage and the stochastic thermal loss component in semiconductor materials, one can greatly increase the charge-conversion efficiency, which impacts the resolution of sensing devices, such as the particle detection application targeted, and the energy efficiency of energy harvesting materials, such as those used in solar-cells.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The higher spectroscopic performance in a radiation-hard package allows one to better correlate the solar particle emissions with the driving feature near the photosphere, thus helping to identify the origins and causes of the solar wind and the Sun’s magnetic field. Thus future NASA heliophysics missions will gain far greater specificity in mapping the solar-driven particles. Beyond heliophysics, fine energy resolution can be used to precisely characterize atmospheric and soil samples captured and ionized during planetary studies.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

For the sensing of optical photons and nuclear radiation, the successful development of a low cost, high performance material will stand as a viable alternative to both single crystal semiconductors and scintillator-based detectors. Thus, optical cameras, medical imaging instruments, military radiation instruments, and rad-hard nuclear power would all be impacted by the successful development.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z4.05-6355
SUBTOPIC TITLE:
 Nondestructive Evaluation (NDE) Sensors, Modeling, and Analysis
PROPOSAL TITLE:
 Probability of Detection and Validation for Computed Tomography Processes for Additive Manufacturing (20-RD-231)
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
UES, Inc.
4401 Dayton-Xenia Road
Dayton, OH 45432
(937) 426-6900

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Veeraraghavan Sundar
E-mail:
vsundar@ues.com
Address:
4401 Dayton-Xenia Road Dayton, OH 45432 - 1894
Phone:
(937) 429-6900

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ms. Louise Tincher
E-mail:
ltincher@ues.com
Address:
4401 Dayton-Xenia Road Dayton, OH 45432 - 1894
Phone:
(937) 426-6900
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

X-ray computed tomography (CT) is a widely used nondestructive evaluation (NDE) method for quality control and post-build inspection in additively manufactured (AM) components. The limitations of such NDE methods and the need to validate the capability of these methods on an ongoing basis are increasingly recognized. Automated, metallography-based serial sectioning offers a reliable method to establish ground truth data on the flaw populations as well as microstructural variations of AM components. Such data can be used to validate, and subsequently improve the reliability of NDE methods. UES proposes a project aimed at establishing comparison methods and workflows for validating CT (and potentially other NDE data) with ground truth from serial sectioning, and developing probability of detection (POD) curves. The knowledge gained from these efforts will inform CT scan strategies for improved flaw detection in AM components, evaluate flaw detectability in CT using serial sectioning as a ground truth comparison, and quantify the risk of the flaws absent from the CT data sets. Phase II extends the work of validation into the area of in situ detection and validation of in situ sensing methodologies using thermal and visual data.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)
  • NASA experimenting with AM across a broad spectrum of applications and projects.
  • AM has potential applications in the Lunar and Lagrange FabLabs, as well as the Mars Multi-Material FabLab for self sustainment at remote destinations 
  • Improving AM via NDE has positive implications for 100% inspected directives on Orion missions.

 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)
  • Reliable NDE/NDI of completed components remains a barrier to wider utilization of AM components. 
  • Limitations in the availability of probability of detection (POD) data will drive wider adoption of AM.
Duration: 6

PROPOSAL NUMBER:
 20-1- H3.03-6356
SUBTOPIC TITLE:
 Lunar Dust Management Technology for Spacecraft Atmospheres and Spacesuits
PROPOSAL TITLE:
 In-situ optical speciation and size distribution monitoring instrument for lunar dust management
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Applied Particle Technology, Inc.
4340 Duncan Avenue, Suite 208
Saint Louis, MO 63110
(650) 288-9061

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Tandeep Chadha
E-mail:
tchadha@appliedparticletechnology.com
Address:
8014 Kingsbury Blvd, Apt 8 Saint Louis, MO 63105 - 3748
Phone:
(314) 956-5909

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Jiaxi Fang
E-mail:
jfang@appliedparticletechnology.com
Address:
519 Sandlewood Street Menlo Park, CA 94025 - 1374
Phone:
(650) 288-9061
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

To support NASA’s needs for environmental particulate matter monitoring, Applied Particle Technology is proposing the development of a multiwavelength optical speciation technology to measure airborne particulate matter size and concentration along with speciation data in a compact low power system. The basis for this technology is the development of an innovative multiwavelength ensemble measurement in combination with an optical particle counter to provide particle size distribution data and identification of aerosol material using optical speciation. Previous prototypes measured particle size distributions up to 10 micrometers, mass concentrations for PM2.5 and PM10, while identifying the particle material as light scattering or light absorbing. The focus of this Phase 1 work will be to mature this technology through broader capabilities of particulate matter speciation for smoke, lunar dust, and general dust, by improving multiwavelength sensor designs and integrating with a dynamic flow control system. Results from this work will enable a Phase II project for an integrated robust, miniaturized, low power instrument capable of speciating smoke, lunar dust, and general dust for microgravity, reduced gravity, and reduced pressure environments.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Environmental particulate matter monitoring with speciation capabilities is a highly sought after capability for applications on the International Space Station and other spacecraft atmospheres. Future missions to the Moon and Mars can benefit from this technology to help manage cleanliness levels and dust intrusion in airlocks and main cabin areas.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Potential non-NASA applications include environmental air quality and climate research, industrial air quality monitoring, smart city monitoring, mining, oil and gas, and manufacturing. Derivatives of this technology can be used to develop innovate sensing products for source apportionment and exposure monitoring.

 

Duration: 6

PROPOSAL NUMBER:
 20-1- S4.05-6362
SUBTOPIC TITLE:
 Contamination Control and Planetary Protection
PROPOSAL TITLE:
 Rapid Microbial Detection and Monitoring Technology for Planetary Protection
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
HJ Science & Technology, Inc.
820 Heinz Avenue
Berkeley, CA 94710
(408) 464-3873

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Homayun Mehrabani
E-mail:
h.mehrabani@hjsciencetech.com
Address:
820 Heinz Avenue Berkeley, CA 94710 - 2753
Phone:
(510) 364-9872

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Hong Jiao
E-mail:
h.jiao@hjsciencetech.com
Address:
820 Heinz Avenue Berkeley, CA 94710 - 2753
Phone:
(408) 464-3873
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

HJ Science & Technology Inc. proposes to develop a fully integrated and automated instrument for performing rapid detection and monitoring of microbes on surfaces and air environments. This technology supports NASA’s Planetary Protection goals of protecting solar system bodies from biological contamination as well as protecting Earth from life forms possibly returned from those extraterrestrial bodies. Specifically, the proposed instrument autonomously and rapidly enumerates bioburden on surface and air environments of cleanrooms, spacecrafts, and payload hardware. In addition to measuring the total number of microbes, the instrument distinguishes between microbe states, such as viable organisms or spores, relevant in Planetary Protection practices. This instrument stems from our novel ChargeSwitch Concentration and Purification (CSCP) technology that bridges the gap between large volume sample processing and small volume genomic detection without sacrificing cell capture efficiency. In Phase I, we will integrate our previously developed CSCP prototype with sample processing and qPCR to quantify microbes on surface and air environments, as well as to differentiate between viable organisms and spores within the sample. In Phase II, we will construct and deliver a fully integrated prototype for autonomous microbial monitoring.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed microbial detection instrument is ideal to support the Planetary Protection’s goal of reducing cross-contamination of terrestrial and possible extraterrestrial life forms by rapidly quantifying bioburden during preparation of spacecraft and autonomously monitors microbes during missions to and from extraterrestrial bodies. Planetary Protections engineers can rapidly validate cleanliness of spacecraft hardware and assembly areas, improve decontamination based on real-time data, and autonomously monitor contamination during missions.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed microbial detection instrument is naturally suited for pathogen detection and monitoring in water and food supply industries on Earth. Moreover, the autonomous monitoring capability of our proposed instrument is ideal for cleanroom monitoring in manufacturing or pharmaceutical environments.

Duration: 6

PROPOSAL NUMBER:
 20-1- H10.01-6364
SUBTOPIC TITLE:
 Advanced Propulsion Systems Ground Test Technology
PROPOSAL TITLE:
 Advanced Computational Tools for Thermal and Acoustic Analysis of Rocket Ground Test Facilities
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Tetra Research Corporation
1019 Cider Mill Road
Cornwall, VT 05753
(256) 426-0056

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Rex Chamberlain
E-mail:
rex@tetraresearch.com
Address:
1019 Cider Mill Road Cornwall, VT 05753 - 9412
Phone:
(256) 426-0056

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Rex Chamberlain
E-mail:
rex@tetraresearch.com
Address:
1019 Cider Mill Road Cornwall, VT 05753 - 9412
Phone:
(256) 426-0056
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Advancements in rocket propulsion system development evolve through the use of safe, reliable and cost-effective ground tests that reduce space propulsion system risk.  The maintenance and improvement of essential ground test facilities that replicate launch and staging environments represent investments that enable meeting National space exploration and commercial use goals.  Innovative software tools that offer improved analysis methods for minimizing program test cost, time and risk while meeting environmental and safety regulations and are thus necessary for supporting state-of-the-art propulsion system test facilities.  The deleterious environment experienced by test structures and components during rocket engine tests may be mitigated by a water suppression system which rapidly injects a large volume of water into the rocket plume to reduce thermal and acoustic loads.  The proposed innovation offers improved techniques for analyzing water suppression mitigation by developing a collection of specialized numerical approaches that accurately capture and handle the behavior of the gas/liquid water interface during water injection.  The proposed approach will improve predictions across a range of scales to model more accurately the liquid jet behavior and its transition to droplets and vapor (to address thermal loading) and its interaction with shocks and turbulent eddies (for acoustic loading).  The advanced tools proposed here offer the ability to design and analyze water suppression systems and the resulting spray patterns to reduce significantly facility maintenance and operating costs while improving safety, reliability and environmental impact.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Advanced water suppression analysis techniques for propulsion systems ground test facilities offer the potential for reductions in facility maintenance and test costs, improvements in platform and test hardware load predictions and more extensive environmental assessments.  The proposed liquid injection analysis tool is also applicable to liquid rocket engines and spray coating processes.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The ability to robustly model complex liquid injection and gas/liquid interface dynamics will allow the commercial aerospace and defense industries to improve design and development of new products involving injection and spray processes.  Our analysis software can also be applied to liquid rocket engines, spray coating processes and biomedical applications.

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.05-6061
SUBTOPIC TITLE:
 Detector Technologies for UV, X-Ray, Gamma-Ray Instruments
PROPOSAL TITLE:
 Novel, Deep-UV APDs for Atomic Clocks and Space Observation
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Adroit Materials
2054 Kildaire Farm Rd., Suite 205
Cary, NC 27518
(919) 515-8637

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Ronny Kirste
E-mail:
ronny@adroitmatrials.com
Address:
2054 Kildaire Farm Rd., Suite 205 Cary, NC 27518 - 6614
Phone:
(919) 515-8637

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Zlatko Sitar
E-mail:
zlatko@adroitmaterials.com
Address:
2054 Kildaire Farm Rd., Suite 205 Cary, NC 27518 - 6614
Phone:
(919) 515-8637
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

The target of this project is to develop a compact and efficient avalanche photodiode (APD) based on Al-rich AlGaN to replace currently used photomultiplier tubes in atomic clocks. The advance over existing approaches is the implementation of single crystal AlN as substrates, which practically eliminates leakage induced by threading dislocations as seen in AlGaN films grown on traditionally employed foreign substrates, such as sapphire and SiC. This enables unprecedented high gain and low noise for the UV detectors. We aim to demonstrate sensitivity over the whole deep-UV range (120 – 200 nm) while being solar and visible blind. We will provide single APDs as well as detector arrays with varying pixel resolution and pixel size. The devices will exhibit very high efficiency (> 40%) and dynamic range with sub-100 V operation. The feasibility of Geiger mode operation and photon counting will also be studied. In addition, we aim to demonstrate high linear gain and avalanche operation by relying on hign probability of electron and low probability of hole ionization for Al molar fractions exceeding 80%. When implemented into Hg-based atomic clocks, as developed for the deep space atomic clocks program, the novel APDs can lead to a significant improvement of the stability and lifetime, while at the same time reduce the volume and constraints of the accompanying electronic circuitry.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

We will develop solar blind avalanche photodiodes with sensitivity in the deep-UV to replace currently-used photomultiplier tubes (PMTs) in atomic clocks being developed for the deep space program. These new detectors will be smaller, more stable, lighter, and have longer lifetime than PMTs. The novel detector will also be arranged in large 2D arrays, which will enable application for space observation such as proposed in LUVOIR, for plume detection, and for bio-chem detection applications.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The novel detector will find application in the military, research, and commercial sector for example in bio-chem detections system, for spectroscopy applications, non-line-of-sight communication, solar blind fire detection, and nuclear detection.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z8.06-6392
SUBTOPIC TITLE:
 DragSails for Spacecraft Deorbit
PROPOSAL TITLE:
 Bi-Fold Fan DragSail with Surface Area Modulation Capability
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Nexolve Holding Company, LLC
290 Dunlop Boulevard, Southwest, Suite 200
Huntsville, AL 35824
(256) 337-6752

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
James Pearson
E-mail:
jim.pearson@nexolve.com
Address:
290 Dunlop Boulevard, Southwest Suite 200 Huntsville, AL 35824 - 1128
Phone:
(256) 971-7027

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Paul DuPre
E-mail:
paul.dupre@nexolve.com
Address:
290 Dunlop Boulevard, Southwest Suite 200 Huntsville, 35824 - 1128
Phone:
(256) 836-7785
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

A new passive reentry system is proposed for deorbiting spacecraft from low earth orbit (LEO).  The proposed DragSail system is based upon a restowable and redeployable concept that allows for increase or decrease of surface area thus modulating aerodynamic drag of the system.  Modulation of the drag will allow the system to guide small spacecraft to specific locations at the Von Karman altitude, which is necessary for precision reentry targeting.  The primary objective of this DragSail design is to deorbit small spacecraft from LEO altitudes in 25 years or less using a modular DragSail system with minimal weight and stowage volume.  The proposed DragSail system is based on NeXolve-developed lightweight solar sail and deployment system technologies.  The concept design consists of ultralightweight polyimide thin-film material that is attached to a deployable boom structure to create a flexible DragSail system with shape morphing capability.  A key feature of this DragSail system is its ability to deploy as a 2-D structure and then shape morph into a 3-D structure that allows drag in all orbital orientations.  Another attractive feature of the design is that the system is a self-contained unit that can be attached to many different types of CubeSats and small satellites.

The DragSail system proposed herein is a scalable system that will allow CubeSats and small satellites up to 200 kg to deorbit from altitudes between approximately 700-1100 km in 25 years or less with the potential for similar results up to 2,000 km.  This innovative restowable, redeployable 3-D shape morphing membrane system is capable of increasing cross-sectional area impinging in all positions along an orbital path.  Partial deployment or partial morphing will enable changes in orbital decay rates allowing for collision avoidance as well as targeted atmospheric re-entry.  This 3D shape morphing capability is a significant advantage over flat (2-D) constructions.

 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed DragSail system is clearly relevant to numerous NASA applications.  Some specific NASA applications for the proposed DragSail system include:

  • Multi-Angle Imager for Aerosols (MAIA)
  • Hyperspectral Thermal Imager (HyTI)

Some more general NASA applications include:

  • Numerous NASA Earth Science missions
  • Numerous NASA Technology and Exploration missions
  • NASA 2020 Technology Taxonomy - Passive Reentry Systems for SmallSats subtopic (TX09.1.3)
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Due to the mandated deorbit requirements, almost any future Earth orbiting small satellite or CubeSat is a potential application for the proposed DragSail system.  Some specific Non-NASA applications for the proposed DragSail system include:

  • SpaceX - Starlink program
  • Amazon - Project Kuiper
  • CubeSats and small satellites built by universities and government institutions

 

 

Duration: 6

PROPOSAL NUMBER:
 20-1- H9.03-6399
SUBTOPIC TITLE:
 Flight Dynamics and Navigation Technology
PROPOSAL TITLE:
 Multi-Target Tracking using Random Finite Sets for Rendezvous and Proximity Operations with Non-Gaussian Uncertainties
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Aster Labs, Inc.
155 East Owasso Lane
Shoreview, MN 55126
(651) 484-2084

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Suneel Sheikh
E-mail:
sheikh@asterlabs.com
Address:
155 East Owasso Lane Shoreview, MN 55126 - 3034
Phone:
(651) 484-2084

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Suneel Sheikh
E-mail:
sheikh@asterlabs.com
Address:
155 East Owasso Lane Shoreview, MN 55126 - 3034
Phone:
(651) 484-2084
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

This program will develop an innovative Random Finite Set (RFS)-theory-based software tool for Multi-Target Tracking (MTT), using measurement filtering methods that include the Sequential Monte Carlo Generalized Labeled Multi-Bernoulli (SMC-GLMB) and the Student’s t-Mixture GMLB (STM-GLMB) filters. These MTT methods enable classification and tracking of objects within the field of view of spacecraft, including a target spacecraft for rendezvous, secondary spacecraft, orbital debris, or other planetary bodies. In this program, ASTER Labs’ team will develop RFS-based algorithms that will improve the reliability of sensor measurement gathering, object classification, and target tracking, even in the presence of high levels of non-Gaussian noise. The newly developed RFS-MTT Toolset will integrate RFS-based algorithms with Clohessy-Wiltshire-Hill, Tschauner-Hempel, and Karlgaard relative orbital dynamics equations, sensor and uncertainty models, and non-Gaussian noise-generation methods to form a full software package for simulation and analytical purposes. Orbital trajectory data from databases maintained by NORAD that feature multiple rendezvous maneuvers will be utilized along with noise models to create additional measurement uncertainty. This data will be processed via the developed RFS-MTT Toolset to confirm fidelity of the dynamics models, analyze the RFS-based algorithms, and verify the algorithms’ ability to accurately track targets in high-clutter and high sensor noise environments. Phase I will focus on developing the RFS-MTT Toolset and associated algorithms for simulations and performance assessment in orbital spacecraft rendezvous and proximity operations. The project will also evaluate these algorithms for eventual incorporation into NASA’s existing software tools, e.g. GEONS. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

This RFS-MTT Toolset will be directly applicable to NASA’s spacecraft rendezvous and proximity operations missions. The software will enhance spacecraft multi-target tracking capabilities, to detect other vehicles and objects in the presence of non-Gaussian noise and false positives. The software applies to cargo transport and delivery, satellite servicing, and orbital debris removal, which will improve modeling and performance in an increasingly cluttered space environment, while having broader applicability to aerial and ground vehicles.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The RFS Multi-Target Tracking algorithms apply to systems requiring data-driven solutions for target identification, classification, and tracking in high-noise environments. Non-NASA applications include military hostile satellite tracking, and covert operations. Commercial applications include UAS integration into civilian aerospace, integration onto UGV systems, and pedestrian flow monitoring.

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.04-6401
SUBTOPIC TITLE:
 Sensor and Detector Technologies for Visible, IR, Far-IR, and Submillimeter
PROPOSAL TITLE:
 In-Pixel Neuromorphic Read-Out Integrated Circuit (Neu-ROIC) for Image Sensors for Earth Observation and Remote Sensing
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Banpil Photonics, Inc.
4800 Patrick Henry Drive, Suite 120
Santa Clara, CA 95054
(408) 282-3628

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Achyut Dutta
E-mail:
akdutta@banpil.com
Address:
4800 Patrick Henry Dr. Suite 120 Santa Clara, CA 95054 - 1820
Phone:
(408) 282-3628

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Achyut Dutta
E-mail:
akdutta@banpil.com
Address:
4800 Patrick Henry Dr. Suite 120 Santa Clara, CA 95054 - 1820
Phone:
(408) 282-3628
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 2
Technical Abstract (Limit 2000 characters, approximately 200 words)

This Small Business Innovation Research Phase I project seeks to develop a Neuromorphic Read-Out Integrated Circuit (Neu-ROIC) that will have in-pixel neuromorphic processing and image capturing capabilities. These enable object detection and recognition on-board, allowing less data to transmit to remote or ground station from space. The proposed Neu-ROIC will have substantially high well capacity for high dynamic range and also in-pixel digital conversion capability, high sensitivity for low detector current, integration times from hundreds of microseconds to tens of millisecond, and high temperature operation possibly enabling to replace cryogenic cooling by thermo-electric cooler, and support for both advanced mid-wave infrared (MWIR) and long wave infrared (LWIR) Image Sensors for NASA applications. During Phase I, the Neu-ROIC architecture will be identified, and its configuration will be simulated and designed and demonstrated. The work done in Phase I through simulations, design and demonstration will be extended for full-developed of test chip and its fabrication in Phase II during which the Neu-ROIC will be demonstrated with an IR sensor.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

ESTO SLIT-15, Long Wavelength Infrared Image Sensor for Land Imaging, ESTO ACT-17, Very Long Wavelength Infrared Image Sensor for Earth Science Applications, ESTO ACT-QRS-17, Image Sensor for Earth Radiation Budget Instruments, ESTO InVEST-15, Compact Infrared Radiometer in Space, and ESTO IIP-16, Compact Midwave Imaging System.  Surface Biology and Geology (SBG) Designated Observable, Planetary Missions, NASA/USGS Sustainable Land Imaging Technology (SLIT) program for new LandSat-10 instruments, sensors, components, and measurement concepts

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Security and surveillance, biometrics, machine vision, Agricultural, Traffic, Fire Monitoring, automotive, robotics, Earth observation, remote sensing, and Scientific Imaging. Soldier helmet cams, small UAV cameras, Next Generation Combat Vehicle, Future Vertical Lift, and autonomous military vehicles. Additionally, night vision, surveillance platforms, border patrol, and firefighting.

Duration: 6

PROPOSAL NUMBER:
 20-1- A2.02-5977
SUBTOPIC TITLE:
 Unmanned Aircraft Systems (UAS) Technologies
PROPOSAL TITLE:
 Drone Modular Smart Pallet (DroneMSP)
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
American GNC Corporation
888 Easy Street
Simi Valley, CA 93065
(805) 582-0582

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Stephen Oonk
E-mail:
soonk@americangnc.com
Address:
888 Easy Street Simi Valley, CA 93065 - 1812
Phone:
(805) 582-0582

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Emily Melgarejo
E-mail:
emelgarejo@americangnc.com
Address:
888 Easy Street Simi Valley, CA 93065 - 1812
Phone:
(805) 582-0582
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

To support the advancement of NASA’s Unmanned Aircraft Systems (UAS) technologies, specifically in the areas of: (a) verification, validation, and certification and (b) sensing, perception, cognition, decision making, American GNC Corporation (AGNC) and California State University, Northridge (CSUN) are proposing a new technology referred to as a Drone Modular Smart Pallet (DroneMSP). This smart pallet consists of a reconfigurable sensor suite, flexible interfacing unit, processing with SD-card memory, and power management. The components are housed in a small form-factor and lightweight frame that can be easily attached to and detached from different vehicles. This smart pallet is designed to be plug-and-play for use on low-cost, common commercial drones, instantly granting them with the smart capabilities of multi-modality sensing with data acquisition and online sensor fusion processing. This technology will instantly enable NASA scientists and many other researchers to test and deploy their own algorithms and sensors on commercial drones. The collected data can be input into in-flight processing algorithms but will also be saved in public repositories to facilitate research by diverse groups with the ultimate goal of advancing Urban Air Mobility (UAM) and the testing of technologies as needed for unmanned flight in the National Airspace. For demonstrating the utility of the smart pallet, an object recognition and collision avoidance Use Case is included which shows how the sensor suite can provide data to an algorithm to conduct a task of relevance to UAM. Key innovations include: (1) plug-and-play hardware and software; (2) flight optimized design; (3) embedded cognition with obstacle avoidance and (4) data labeling scheme for sensor quality generation.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The DroneMSP system will advance the state-of-the-art of NASA’s unmanned aircraft systems by facilitating the deployment and testing of sensor payloads with data-fusion and intelligent algorithms. The smart pallet can be adapted for use on quadcopter drones, newer mid-sized designs such as the Langley Aerodome 8, and larger fixed wing unmanned aircraft for airborne remote science measurements. DroneMSP will benefit NASA research in safe and efficient Urban Air Mobility, for which centers such as AFRC, ARC, GRC, and LaRC are actively advancing.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

 

The DroneMSP will improve the ability of universities, laboratories, companies, students, and even hobbyists to conduct UAS research in a practical way. Commercial applications include inspection, agriculture, airborne sensing, surveying, delivery, construction and mining, imaging, etc. Government applications include traffic monitoring, search & rescue, border security, disaster management, etc.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z5.05-6062
SUBTOPIC TITLE:
 Lunar Rover Technologies for In-situ Resource Utilization and Exploration
PROPOSAL TITLE:
 Modeling Rover Interactions with Lunar Regolith in Permanently Shadowed Regions
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Blueshift, LLC
575 Burbank Street, Unit G
Broomfield, CO 80020
(850) 445-3431

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ryan Garvey
E-mail:
rgarvey@outward.tech
Address:
575 Burbank St., Unit G Broomfield, CO 80020 - 7161
Phone:
(850) 445-3431

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ryan Garvey
E-mail:
rgarvey@outward.tech
Address:
575 Burbank St., Unit G Broomfield, CO 80020 - 7161
Phone:
(850) 445-3431
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Blueshift, LLC doing business as Outward Technologies proposes to develop a Discrete Element Method (DEM) modeling framework using open-source software to simulate the combined thermal and mechanical interactions between rovers and regolith in Permanently Shadowed Regions (PSRs) at the lunar poles. This proposed set of numerical tools innovates on the current state of the art by explicitly solving for both thermal and mechanical interactions between rover components and regolith, and by the inclusion of volatiles such as water ice of multiple forms (e.g. vapor deposited “frost”, blocky deposits, and icy regolith mixtures) in a grain-based DEM model. Rover components including probes, drills, wheels, and soil sampling equipment will be simulated using coupled FEM software to reduce computation time. A coupled thermo-hydro-mechanical model will further be explored for its suitability in simulating volatile phase change and gas transport through cryogenic regolith as represented by a bonded-particle DEM. These numerical modeling capabilities will be integrated within a single, easy to use simulation framework for approximating thermal and mechanical interactions between rovers and regolith across ranges of possible conditions which may be encountered in and near PSRs on the Moon. These combined numerical tools will enable NASA and its partners to inexpensively evaluate hardware designs for lunar ISRU missions aimed at exploration and prospecting for volatiles. These improved modeling capabilities will further de-risk planned missions to the lunar south pole by identifying successful control strategies and hardware designs for ISRU sampling, material handling, increased rover operability, and surviving the lunar night, leading to more rugged and capable rovers for lunar polar missions while reducing their costs related to development and testing.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

This project leads to many potential NASA applications including the design and evaluation of rovers and sampling equipment for use in lunar polar regions for ISRU prospecting and exploration missions. The proposed DEM-FEM coupled software and its associated advancements will bring additional knowledge to the challenges faced in lunar polar missions while presenting a low-cost evaluation tool for hardware design, rover control strategies, and volatile sampling. These improvements will lead to lower cost lunar ISRU missions with reduced risk.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

By increasing the sampling of the high-dimensional design space of DEM microscale input selection, Outward Technologies will be able to gain a competitive advantage in thermo-mechanical DEM models related to granular mechanics and will be able to incrementally increase our customer base, tailoring services to companies in the field of powder handling, pharmaceuticals, oil and gas, and mining.

Duration: 6

PROPOSAL NUMBER:
 20-1- S2.01-4661
SUBTOPIC TITLE:
 Proximity Glare Suppression for Astronomical Direct Detection of Exoplanets
PROPOSAL TITLE:
 Specular Black Coating for Flexible Starshade Optical Sheild
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
ZeCoat Corporation
23510 Telo Avenue, Suite 3
Torrance, CA 90505
(424) 254-6002

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
David Sheikh
E-mail:
dsheikh@zecoat.com
Address:
23510 Telo Avenue, Suite 3 Torrance, CA 90505 - 4053
Phone:
(424) 254-6002

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Gillian Sheikh
E-mail:
ggsheikh@zecoat.com
Address:
23510 Telo Avenue, Suite 3 Torrance, CA 90505 - 4053
Phone:
(424) 254-6002
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

ZeCoat Corporation will develop a specular, low reflectance coating with high optical density for a star shade’s light blocking membrane.  The coatings will be applied to polyimide membrane surfaces such as KaptonTM or CP1TM and will be designed to produce very dark and  specular surfaces. The coatings may also be applied directly to rigid substrates such as light baffles.

Low reflectance surfaces are needed for starshades to reduce stray light from entering the telescope from earthshine, moonshine, near-planets, and background stars and galaxies.  A specular membrane will ensure only a small solid angle of light coming from directly behind the telescope can produce stray light. A specular coating will also prevent the reflectance phenomenon known as the "opposition effect", which causes an observed brightening in the retro-direction from coherent backscater off a rough surface.

Existing blackening processes such as carbon nanotubes, copper oxides, carbon-filled KaptonTM, and others, result in rough surfaces that reflect and scatter significant energy.  Many of these three-dimensional surfaces are easily damaged by abrasion (creating particulate contamination), degrade in humidity during ground storage, degrade in the high radiation environments of space, or in the case of black-KaptonTM, are significantly reflective and relatively heavy.  In this SBIR, we will demonstrate the feasibility of creating new materials and processes that alleviate these deficiencies. 

In Phase I polyimide membrane materials will be coated with our batch coating process to demonstrate feasibility.  The batch process utilizes a moving evaporation source and rotating substrate to achieve coating uniformity over a broad area.

In Phase II, we will develop a novel, roll-to-roll process to manufacture precision optical coatings in the quantities needed for future starshades and commercial applications.   

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Starshade membranes, WFIRST, HabEx, LUVOIR, LISA, light suppression for light baffles and optical sensors

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

This technology will help reduce the optical signature of future commercial satellite constellations such as Starlink, which threaten to create excessive light pollution interfering with ground-based telescope observations.

Commercial stray light reduction applications include cell phone cameras, telescope light baffles, and many optical sensor applications.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z4.04-6302
SUBTOPIC TITLE:
 Real Time Defect Detection, Identification and Correction in Wire-Feed Additive Manufacturing Processes
PROPOSAL TITLE:
 Integrated Process Monitoring Software and Multi-Sensor Suite for Improved Reliability in Wire-Fed AM
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Solvus Global LLC
104 Prescott Street
Worcester, MA 01605
(508) 373-2750

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Sean Langan
E-mail:
sean.langan@solvusglobal.com
Address:
104 Prescott Street Worcester, MA 01605 - 1703
Phone:
(224) 406-4536

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Sean Kelly
E-mail:
sean.kelly@solvusglobal.com
Address:
104 Prescott Street Worcester, MA 01605 - 1703
Phone:
(508) 733-1808
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

A fundamental problem with materials and manufacturing at NASA is the need to rapidly, repeatably, and cost-effectively manufacture unique, defect-free, complex parts to build spacecraft at a wide range of size scales. Space vehicles must ensure safety and reliability throughout missions, the durations of which are ever-increasing as the bounds of space are pushed. Therefore, each component used in these vehicles must start with and maintain critical levels of structural integrity.

Additive manufacturing (AM) processes offer a solution to the challenges of manufacturing unique, complex parts rapidly, but can be expensive and error-prone. Powder-based AM processes use expensive and oftentimes hazardous feedstock and produce large amounts of waste material. Wire-based AM processes solve these problems, but are still limited in relation to repeatability, reliability, and the need for inspection to identify defects that significantly reduce part performance.

Solvus Global’s proposed solution is to implement a detection and feedback monitoring software integrated with multiple sensors for defect detection, enabling maximum information and decision-making power for wire-fed AM processes, specifically the high deposition rate Wire Arc AM (WAAM). Solvus Global will utilize their existing AM process monitoring platform, APEX, to collect, store and analyze data from WAAM process parameters and the integrated sensor-suite including laser profilometry and thermal imaging for surface monitoring, arc health analysis, and wire resistivity for feedstock quality assurance. When correlated to process parameters, these methods will improve the consistency of AM processes and establish the foundation for closed-loop control with real-time defect correction. Through this work, Solvus Global will prove the feasibility of using the proposed sensor suite for real-time defect detection during WAAM processing and will determine the path forward towards real-time correction of defects.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Improved repeatability and reliability of AM processes will benefit many of NASA’s high-priority missions and applications, including the Orion crew vehicle, the Space Launch System (SLS), commercial crew and commercial cargo programs, and science missions. Specifically, DRM 5 Asteroid Redirect, DRM 6 Crewed to NEA, DRM 7 Crewed to Lunar Surface, DRM 8 Crewed to Mars Moons, DRM 8a Crewed Mars Orbital, and DRM 9 Crewed Mars Surface Missions will all be enabled by Solvus Global’s technology.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Non-NASA markets for WAAM range from marine and automotive applications to renewable energy, oil & gas, and nuclear sectors. Any unique or complex components that need to be rapidly, repeatably, and cost-effectively manufactured and require structural integrity would benefit from improved reliability and repeatability in AM processes.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z3.03-6207
SUBTOPIC TITLE:
 Development of material joining technologies and large-scale additive manufacturing processes for on-orbit manufacturing and construction
PROPOSAL TITLE:
 More Durable Pin Tools for Friction Stir Welding
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Transition45 Technologies, Inc.
28245 Via Del Mar
San Juan Capistrano, CA 92675
(714) 283-2118

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Edward Chen
E-mail:
t45tech.edward@gmail.com
Address:
28245 Via Del Mar San Juan Capistrano, CA 92675 - 6342
Phone:
(714) 283-2118

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Edward Chen
E-mail:
transition45@yahoo.com
Address:
1739 North Case Street Orange, CA 92865 - 4211
Phone:
(714) 283-2118
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

This SBIR Phase I project will develop a novel processing method for W-Re alloys that will allow for higher performance pin tools for use in friction stir welding (FSW). A solid state process, FSW is fast becoming the process of choice for the manufacture of lighter weight aerospace structures.  As such, it is being considered as an essentially complementary joining capability for on-orbit and space environments. Pin tool technology especially for higher temperature FSW continues to be a major challenge and will limit usage in space if not further advanced. An ideal pin tool should have high toughness, good strength, excellent wear resistance, and be chemically inert at welding temperatures. Tungsten-based tools have good fracture toughness, but are also very expensive and experience severe wear and degradation during high temperature welding. A greatly improved, more cost-effective, and near-net process was developed to process pure W components with refined microstructures. If successfully applied to W-Re alloys to enhance the properties, higher performance pin tools may be possible.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Potential NASA Applications include metal structures and components for space launch vehicles, spacecraft, space habitats, airframes, and gas turbines.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Potential Non-NASA Applications include metal structures and components for military and/or commercial space launch vehicles, spacecraft, airframes, air and land-based gas turbines, land vehicles (cars, trucks, trains), sea vehicles (recreation, passenger, cargo), and consumer products (electronics).

Duration: 6

PROPOSAL NUMBER:
 20-1- H9.07-6063
SUBTOPIC TITLE:
 Cognitive Communication
PROPOSAL TITLE:
 Cross-Layer Wide-Band Cognitive Communications Architecture Enabled by Intelligent Direct Digital Transceiver (CLAIRE)
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
AiRANACULUS
9 Flint St.
Chelmsford, MA 01824
(404) 819-0314

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Apurva Mody
E-mail:
apurva.mody@airanaculus.com
Address:
9 Flint St. Chelmsford, MA 01824 - 2226
Phone:
(404) 819-0314

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Apurva Mody
E-mail:
apurva.mody@airanaculus.com
Address:
9 Flint St. Chelmsford, MA 01824 - 2226
Phone:
(404) 819-0314
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

AiRANACULUS, Northeastern University and NWRA supported by DRAPER propose an innovative Cross-layer Wide-Band Cognitive Communications Architecture Enabled by Intelligent Direct Digital Transceiver (CLAIRE) to meet the NASA's Space Communication and Navigation (SCaN) needs to increase mission science data return, improve resource efficiencies for NASA missions and communication (Comms) networks and ensure resilience in the unpredictable space environment. The CLAIRE cognitive system is envisioned to sense, detect, adapt, and learn from its experiences and environment to optimize the Comms capabilities for the user mission of the network infrastructure. Our Comms Node will reduce both the mission and network operations burden. This will entail research and development of Cross-layer Sensing (CLS) and the CLAIRE Decision Engine (CDE) which uses machine learning over short term and long term along with game theoretic decision to define the strategy and technique to mitigate the interference and restore the network performance. The CLS consists of RF sensing and Cyclostationary-Signal Processing analysis, Cross-layer Feature Extraction and Environment Characterization and Pattern Classification Modules. The CDE consists of the Long-term Response Engine which is driven by the Game-theoretic approaches, and the Rapid Response Engine, which is driven by Deep Reinforcement Learning (DRL) techniques. We propose to use of Supervised DRL Model Selection and Bootstrap for rapid bootstrapping. Finally, we also propose to conduct research into new state-of-the-art Direct Digital Transceiver (DDTRX) Technologies for potential application for NASA’ s mission. Latest advances in the DDTRX Technology provide sampling rates of 64 Gsps, instantaneous bandwidths of 20 GHz with four coherent channels and 8-bits per sample of quantization. This allows us to use any spectrum from VHF/UHF to Ku/ Ka Band on a single radio which will reduce the SWAP and could be of great interest to NASA.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

CLAIRE allows NASA to combine the advanced Cognitive Cross-layer Optimization with the latest breakthroughs in the Direct Digital Transceiver (DDTRX) technology. We anticipate CLAIRE to benefit the following applications: (1) Cross-layer approaches for optimum communication (Comms) (2) Efficient use of lunar Comms spectrum and interference mitigation (3) Integrated wide-band sensing and narrow-band Comms on the same radio. (4) Implementation of artificial intelligence and machine learning techniques on SWaP-constrained platforms (5) Lower SWAP.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Potential Non-NASA Applications include: (1) Commercial 5G and Next G communications, (2) Military cognitive communications (3) wide-band sensing and signals intelligence (4) Radar and LIDAR Applications for motion and proximity detection (5) Cross-layer optimization (6) Machine learning on large data sets etc. 

Duration: 6

PROPOSAL NUMBER:
 20-1- A1.07-6328
SUBTOPIC TITLE:
 Propulsion Efficiency - Turbomachinery Technology for High Power Density Turbine-Engines
PROPOSAL TITLE:
 A GPU-Accelerated Full-Wheel Multi-Stage Turbomachinery Flow Solver
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
CASCADE Technologies, Inc.
2445 Faber Place, Suite 100
Palo Alto, CA 94303
(650) 521-0243

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Kan Wang
E-mail:
kwang@cascadetechnologies.com
Address:
2445 Faber Place, Suite 100 Palo Alto, CA 94303 - 3346
Phone:
(574) 309-5898

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Guillaume Bres
E-mail:
gbres@cascadetechnologies.com
Address:
2445 Faber Place, Suite 100 Palo Alto, CA 94303 - 3346
Phone:
(650) 521-0243
Estimated Technology Readiness Level (TRL) :
Begin: 4
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

Cascade will validate the CPU-based moving mesh solver using NASA stage 37, high-pressure-ratio stage of an axial core compressor developed by NASA in late 1970’s. Cascade will port its moving version of the large-eddy simulation (LES) flow solver charLES to GPU-accelerated architectures. The moving mesh solver uses the same Voronoi diagram-based meshing strategy as the static mesh solver, however the meshing is now integrated with the solver to allow local regeneration of the Voronoi diagram when points are in relative motion. The current implementation for traditional architectures uses a conservative space-time formulation that allows for complex motions including collisions and full contact. Since complex motions and thus complex solver treatments are not required for the relatively simple solid-body rotational motion of turbomachinery, the development will be staged by first porting the Voronoi point search and cutting algorithms to the GPU, and simply re-cutting the interface cells in each time step, and updating the communication pattern. The entire algorithm can remain fully explicit, utilizing essentially the same solver as the static charLES for accelerated architectures. In regards to specific architectures, the static accelerated charLES is written in both CUDA and HIP, allowing us to leverage both NVIDIA and AMD accelerated architectures. Verification will be performed by comparing the GPU and CPU implementations in two stages. First, a comparison of the geometric data and operators (e.g. geometric conservation, volumetric fluxes and gradient operators) will be conducted on a mesh containing a moving disk part. Second, a comparison of the flow variables will be made on canonical flows (e.g. Euler vortex, 1D acoustic wave and solid body rotation) with and without a moving disk part. The moving solver calculations will be validated by comparing results against a direct numerical simulation of a rotating sphere.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The GPU-accelerated mesh generator could eventually evolve into stand-alone meshing tool. Leveraging the duality between the Voronoi diagram and the Delaunay triangulation, the tool can quickly produce tetrahedral meshes for NASA codes (e.g., FUN3D). The GPU-accelerated moving mesh solver and its capability of performing efficient full-annulus multi-stage simulations of compressors and turbines will benefit NASA’s turbomachinery research by providing a high-fidelity simulation approach to complement NASA’s RANS codes (e.g. APNASA and TURBO).

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Turbomachinery is at the core of the aeronautical propulsion. The successful completion of Phase I & II will produce an efficient and affordable solution for high-fidelity numerical predictions of complex flows in compressors and turbines, which is highly aligned with the request and demand of Cascade’s commercial licensees in the aerospace industry (e.g. Bosch, Boeing and General Electric).

Duration: 6

PROPOSAL NUMBER:
 20-1- A1.01-4698
SUBTOPIC TITLE:
 Aeroelasticity and Aeroservoelastic Control
PROPOSAL TITLE:
 Generation of CFD-Based Structurally Independent Aerodynamic Influence Coefficient Matrix
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
ZONA Technology, Inc.
9489 East Ironwood Square Drive
Scottsdale, AZ 85258
(480) 945-9988

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ping-Chih Chen
E-mail:
pc@zonatech.com
Address:
9489 East Ironwood Square Drive Scottsdale, AZ 85258 - 4578
Phone:
(480) 945-9988

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Jennifer Scherr
E-mail:
jennifer@zonatech.com
Address:
9489 East Ironwood Square Drive Scottsdale, AZ 85258 - 4578
Phone:
(480) 945-9988
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Despite advances in Computational Fluid Dynamics (CFD) methods; application of CFD to an aeroelastic analysis is still not well-accepted by the aerospace industry. Currently, the unsteady panel methods still are the major workhorse used by the aerospace industry because these panel methods can generate the Aerodynamic Influence Coefficient (AIC) matrix. The AIC matrix is a multi-input-multi-output aerodynamic transfer function. Because it is an aerodynamic transfer function, the AIC matrix is independent of the structure and only depends on the aerodynamic geometry. Thus, once the aerodynamic configuration is fixed, the AIC matrix can be repeatedly used for structural design. However, because of the linear potential flow assumption, the unsteady panel methods are not valid at transonic Mach numbers. In these flow conditions, accurate unsteady aerodynamic forces can only be obtained by solving the Euler or Navier-Stokes equations. Therefore, the aerospace industry would greatly benefit from having an innovative method that can efficiently generate the AIC matrix from the CFD methods.

The overall technical objective of this Phase I effort is to develop a CFD-based AIC generator to generate the structurally independent AIC matrices using high fidelity CFD codes. Using these AIC matrices, the generalized aerodynamic forces (GAF) can be rapidly computed for performing aeroelastic analysis. With a small computational effort, the AIC matrices also can generate the GAFs due to control surface kinematic mode and gust excitation.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)
The Phase I effort is highly relevant to on-going and future NASA's fixed wing projects that involves several non-conventional design concepts such as the Blended Wing Body (BWB), and Supersonic Business Jet (SBJ). Because of the BWB's flying wing-type and the SBJ's slender fuselage designs, these designs are prone to the Body Freedom Flutter problem. The proposed work will offer a computational tool to the NASA designers for rapidly performing aeroelastic analysis throughout the structural design cycles of these non-conventional design.
 
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Aircraft structural design requires flutter, aeroservoelastic (ASE), and gust analysis. Aeroelastic problems usually occur in the transonic flow regime at which the unsteady aerodynamics solved by the unsteady panel methods are not accurate. The proposed CFD-based AIC generator, once developed, will be well accepted by all aerospace companies.

Duration: 6

PROPOSAL NUMBER:
 20-1- A3.03-4970
SUBTOPIC TITLE:
 Future Aviation Systems Safety
PROPOSAL TITLE:
 Weather Sensor and Data Monitoring (WSDM) Service
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Resilienx
235 Harrison St, Ste #203
Syracuse, NY 13202
(315) 286-1599

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Greg Dorchies
E-mail:
g.dorchies@resilienx.com
Address:
235 Harrison St, Ste #203 Syracuse, NY 13202 - 3023
Phone:
(603) 831-1888

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ryan Pleskach
E-mail:
ryan.pleskach@resilienx.com
Address:
235 Harrison St, Ste #203 Syracuse, NY 13202 - 3023
Phone:
(315) 286-1599
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Safe airspace and operations depend on accurate weather data to make critical decisions, plan fleet asset taskings, schedule cargo or people movements, and meet client expectations.  More reliance on automation means there are less nodes in the workflow where humans can identify anomalies in data.

ResilienX is proposing to develop a Weather Sensor and Data Monitor (WSDM) service that we will integrate into our commercial In-time System-wide Safety Assurance (ISSA) platform; FRAIHMWORKTM (Fault Recovery and Isolation, Health Monitoring frameWORK). The goal of the WSDM is to detect when a weather source is not providing valid data. Weather sources may be IoT sensors, cameras, crowd sourced data, radar data, or even national, academia and private sector weather feeds. We will focus this effort on low altitude, urban environments that have specific complex micro-weather challenges and enable the accelerated deployment of an initial urban wind model capability.

We will monitor and enhance these weather sources by creating a micro-weather model for the urban environment which considers the structure (i.e. building and terrain) using Computational Fluid Dynamics as well as meteorology at low altitude. Since the weather data and forecasts are based off the input data to this model, verifying the validity of the input data will enable trust of the output.

Our vision is to enhance our ISSA platform with an advanced low altitude urban weather model capable of detecting and predicting “hot spots” that drones should stay away from. This initial model will accelerate commercialization of an important data set to identify hazard areas and keep airframes and people safe as we test, demonstrate, and deploy initial UAS and UAM operations in urban environments. We will also provide the capability to verify inputs to this model and identify misbehaving sensors before they have the chance to put bad data in and potentially affect the model.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

This initiative enables NASA applications that depend on highly reliable and persistent non-government space, atmospheric and terrestrial measurements and predictions:

  • Commercial space launches and human space travel
  • ATM / UAS / UTM / UAM Systems, Industries, and Projects
  • Satellite and communication systems

UAS and UAM is a “blue sky” mission area to demonstrate how weather systems and weather monitoring, especially in urban areas, can reduce the impact of anomalous events to mission critical operations.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Our applications for this technology extend to FAA and commercial endeavors of the same mission areas that NASA is working in, namely:

  • Commercial space launches and human space travel
  • ATM / UAS / UTM / UAM 
  • Satellite and communication systems

We are also looking at how cities can use urban micro weather data as part of Smart City initiatives by deploying IoT weather sensors.

Duration: 6

PROPOSAL NUMBER:
 20-1- A1.02-5606
SUBTOPIC TITLE:
 Quiet Performance - Aircraft Propulsion Noise
PROPOSAL TITLE:
 Unstructured Overset Hybrid RANS/LES Simulations for Jet Noise Prediction
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Scientific Simulations, LLC
1582 Inca Drive
Laramie, WY 82072
(307) 399-0871

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Enrico Fabiano
E-mail:
enrico@scientific-sims.com
Address:
1582 Inca Drive Laramie, WY 82072 - 5007
Phone:
(307) 761-3829

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dimitri Mavriplis
E-mail:
mavripl@scientific-sims.com
Address:
1582 Inca Dr. Laramie, WY 82072 - 5007
Phone:
(307) 399-8717
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

The objective of this proposal is the development and demonstration of an efficient scale-resolving aeroacoustic approach for the prediction of noise generated by installed engine configurations. The development of new engine concepts has traditionally relied on inexpensive low and mid-fidelity methods combined with expensive experimental campaigns. Scale-resolving simulations offer a cost-effective alternative to model testing. In this Phase 1 proposal we seek to demonstrate the efficiency and accuracy of our dual-mesh, dual-solver overset strategy for jet-noise aeroacoustics. An efficient unstructured mesh solver is used to resolve the flow near the nozzle, while our high-order, adaptive, Cartesian mesh DG solver is used to resolve the acoustic waves in the jet-plume region. The DDES approach is used to model the turbulent jet flow. The temporal evolution of the nozzle flow is used as input to a source-time-dominant implementation of the Ffowcs-Williams Hawkings (FW-H) equation to determine the jet’s noise spectra at far-field observers. The acoustic integration will be performed on a permeable surface that encloses the noise-generating turbulent structures in the jet. Additionally, the feasibility of the volume integration of the quadrupole term in the FW-H equation will be investigated. This Phase-1 work will target the prediction of the noise generated by an isolated round jet. The accurate prediction of the noise spectra at far-field observers will demonstrate the feasibility of our high-order, adaptive, overset noise-prediction strategy. The established noise-prediction methodology will be further refined and used in the second phase of this project to predict the noise generated by complex, installed engines configurations. Our overset mesh paradigm is well suited for complex geometries, and our successful implementation of the quadrupole term will resolve the uncertainties in choosing suitable FWH integration surfaces.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed techniques will provide a novel cost-effective high-fidelity tool for jet noise prediction. This is an important application area for the NASA Aeronautics Mission Directorate, since the acceptance of future commercial aircraft depends heavily on reduced environmental impact including take-off and landing noise requirements. Our surface integration FWH code as well as our volume integration quadrupole code will be written in a modular fashion which will be delivered to NASA for inspection and coupling with internal NASA codes.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The high-fidelity, overset jet-noise prediction strategy will complement our ongoing work with lower fidelity RANS-based approaches for design optimization of jet noise metrics.  The developed noise-prediction capability will be marketed by Scientific Simulations LLC to current and potential new customers as a suite of progressively increasing fidelity tools with add-on aeroacoustic capabilities.

Duration: 6

PROPOSAL NUMBER:
 20-1- H12.05-6577
SUBTOPIC TITLE:
 Autonomous Medical Operations
PROPOSAL TITLE:
 Intelligent Medical Crew Assistant (IMCA)
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Tietronix Software, Inc.
1331 Gemini Avenue, Suite 300
Houston, TX 77058
(281) 461-9300

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
William Buras
E-mail:
william.buras@tietronix.com
Address:
1331 Gemini Avenue, Suite 300 Houston, TX 77058 - 2794
Phone:
(281) 461-9300

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Frank Hughes
E-mail:
fhughes@tietronix.com
Address:
1331 Gemini Avenue, Suite 300 Houston, TX 77058 - 2794
Phone:
(281) 461-9300
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Our proposed concept is the Intelligent Medical Crew Assistant (IMCA), which is an intuitive, adaptive, voice-interactive intelligent user interface that functions as a virtual medical officer to enable enhanced crew medical autonomy.  By developing this important front-end technology, IMCA promises to seamlessly integrate these tools and resources to support longitudinal crew monitoring, health maintenance, medical care and emergency response as well as optimization of resources for long-duration human spaceflight. IMCA, utilizes an integrated set of technological brick components aimed at providing support to the crew with respect to medical operations. The first component is a Dialog based/Voice enabled intelligent assistant with Natural Language Processing and intents identification. Crew can ask any question with respect to the medical procedures, inventory of medical supplies, their health monitoring, and recommended counter measures. The second technology brick is an AR enabled Electronic Procedures platform containing a repository of the medical procedures, an execution engine, an Augmented Reality device and software to guide the crew during the procedure execution. This component is able to provide Just-in-Time Training (JITT) for medical procedures using AR or/and VR glasses. A third brick is an Adaptive User Interface, adapting training or procedure execution to the level of expertise and cognitive workload of the crew. Our IMCA integrates with the EHR/EMR and medical inventory system in to monitor the health of the astronauts and help them identify resources needed for medical procedures. Machine Learning algorithms provide indications adverse medical conditions using individual crew health monitoring data. By having the data and procedural guidance when they need it, in a format optimized to each respective crewmembers skills and UI/UX preferences, crew will be able to more effectively operate autonomously and achieve both health hand mission goals.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA's human space exploration strategy and program of innovative robotics missions challenges engineers to develop new and complex systems with advanced capabilities.  Human Health and Performance is a key feature and medical systems required to support Astronauts significantly increases in complexity. The Phase I concept will be developed to support multiple types of ultrasound procedures, and the suite of Just-In Time AR tools. The tool can be used for the International Space Station, Small Pressurized Rover, NEMO iPAS, HESTIA, and CDS 2.0.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Tietronix has already initiated work with Methodist Houston to initiate clinical trials of eVULCAN for Covid 19 rapid training and biocontainment enhancement through intra-institution telemedicine. Tienovix (the company licensing eVULCAN IP) has applied for FDA emergency authorization for such use. First trails are expected to start in May/June 2020. 

Duration: 6

PROPOSAL NUMBER:
 20-1- H3.01-6430
SUBTOPIC TITLE:
 Advancements in Carbon Dioxide Reduction: Critical Subsystems and Solid Carbon Repurposing
PROPOSAL TITLE:
 Efficient Particulate Carbon Filtration for Space Oxygen Recovery Using Catalytic Nanoarray-Based Porous Metal Monolithic Filters
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
3D Array Technology
1392 Storrs Road, ATL Building, Room 102
Storrs, CT 06269
(860) 944-3870

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Xingxu Lu
E-mail:
xingxu.lu@3-dat.com
Address:
125 South Street 318 Vernon, CT 06066 - 4456
Phone:
(860) 771-9905

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Sibo Wang
E-mail:
sibo.wang@3-dat.com
Address:
169 Vernon Avenue., 91 Vernon, CT 06066 - 4370
Phone:
(860) 944-3870
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

In order to achieve the long duration manned deep-space missions, NASA created the Spacecraft Oxygen Recovery (SCOR) project aiming to increase the oxygen recovery of the Sabatier technology from 50% to 75-100%, and the Game Changing Development Program has been seeking techniques addressing “Advanced Oxygen Recovery for Spacecraft Life Support Systems”. Space oxygen recovery technologies implemented include carbon formation reactors (CFR) and methane pyrolysis assembly (PPA) reactors. These technologies, however, almost universally result in the formation of particulate carbon, which could undermine the operation of the spacecraft and threaten crew safety. Therefore, this proposed project directly addresses the needs of the subtopic H3.01: Advancements in Carbon Dioxide Reduction: Critical Subsystems and Solid Carbon Repurposing. The overall objective of the proposed project is to develop a new class of catalytic nanoarray-based monolithic filters to achieve the efficient filtration of particulate carbon for space oxygen recovery by integrating catalytically active nanostructured arrays onto the porous metal particulate filters. During the filtration process, the conformal nanoarray forests can increase the filtration efficiency while maintaining a low-pressure drop. Meanwhile, the nanoarray-supported catalysts can motivate the carbon gasification reaction and achieve fast filter regeneration at low temperatures. The proposed particulate filter could also completely avoid crew exposure to the accumulated carbon particulates. This project, if completed, will enable NASA to remove and manage the particulate carbon in the space station in a more efficient way with a more space compact, light-weighted, energy-efficient, and easily regenerable filtration device.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed nanoarray-based monolithic filter is designed for the filtration of carbon particulate emissions from the plasma pyrolysis assembly for methane decomposition, but it could also be used to remove different particulate contaminant in other areas of the space stations.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The nanoarray-based monolithic filters will provide an energy-efficient, cost-effective, space compact and easily regenerable technology to remove particulate matters in different applications. For example, it can be employed as particulate filters used in industrial plants, power stations, and commercial buildings. It may also be used to control particulate emissions from automotive vehicles.

Duration: 6

PROPOSAL NUMBER:
 20-1- S4.05-6431
SUBTOPIC TITLE:
 Contamination Control and Planetary Protection
PROPOSAL TITLE:
 Plasma-Based Techniques for Spacecraft Contamination Control
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
CU Aerospace, LLC
3001 Newmark Drive
Champaign, IL 61822
(217) 239-1703

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Joseph Zimmerman
E-mail:
jwzimmer@cuaerospace.com
Address:
3001 Newmark Drive Champaign, IL 61822 - 1474
Phone:
(217) 239-1702

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
David Carroll
E-mail:
carroll@cuaerospace.com
Address:
3001 Newmark Dr Champaign, IL 61822 - 1474
Phone:
(217) 239-1703
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

In this NASA Phase I SBIR, CU Aerospace and the University of Illinois Microbiology Department will partner to develop compact sterilizers based on plasma-generated Reactive Oxygen Species (ROS) technology.  Specifically, the team will apply radio frequency electric discharges operating at moderate pressure (5-50 Torr) in O2:He mixtures to generate significant quantities of reactive species, especially singlet delta oxygen, referred to as O2(a), a known sterilant of various microorganisms.  The afterglow exhaust from the plasma generator will be flowed over samples of spores (e.g. G. stearothermophilus), and the inactivation rate of the spores at various plasma reactor settings will be determined.  Various reactive oxygen species (electronically-excited singlet O2, O atoms, ozone) produced in the plasma reactor will be characterized while flow temperatures will be monitored spectroscopically, and these results will be used to derive exposure conditions suitable for sterilization of various spacecraft materials. A methodology for quantifying bacteria inactivation on various materials will be devised. The team will develop a preliminary design for a prototype demonstration unit which simulates an in-situ sterilizer configuration for validating application on exploration missions.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

In response to spacecraft contamination concerns, the proposed work will develop procedures, techniques, and a knowledge base for aiding in validation of plasma-generated ROS for decontamination roles on future missions. Envisioned roles are: (1) sterilization of spacecraft components prior to deployment, (2) in-situ treatment of sampling tools prior to collection, (3) treating bio-containers prior to return-sample collection and container exteriors prior to stowage, and (4) use on manned missions for science tools and medical equipment.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The plasma-generated ROS technology has strong potential for low-temperature sterilization needs in the healthcare industry, and others such as wearable consumer electronics, where decontamination is necessary. A target application for closed-cycle operation of the proposed technique is a compact sterilization chamber for medical equipment and personal protective equipment (PPE).

Duration: 6

PROPOSAL NUMBER:
 20-1- S3.02-6450
SUBTOPIC TITLE:
 Dynamic Power Conversion
PROPOSAL TITLE:
 Energy Buffer Capacitors for Use in Dynamic Power Conversion ACUs
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Sigma Technologies International, Inc.
10960 North Stallard Place
Tucson, AZ 85737
(520) 575-8013

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Angelo Yializis
E-mail:
ayializis@sigmalabs.com
Address:
10960 North Stallard Place Tucson, AZ 85737 - 9527
Phone:
(520) 575-8013

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Christopher Hohmann
E-mail:
chohmann@sigmalabs.com
Address:
10960 North Stallard Place Tucson, AZ 85737 - 9527
Phone:
(520) 575-8013
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

This NASA Phase I SBIR proposal addresses the development of energy buffer capacitors to replace multilayer ceramic (MLC) capacitors used in the advance controller unit (ACU), of dynamic power conversion systems.  Dynamic power conversion systems designed for long duration deep space missions, require stable and reliable ACUs to precisely control the function of the energy conversion system and provide DC power to the spacecraft.  MLCs have poor capacitance stability with temperature, voltage and time on voltage.   This development proposes to design, produce and evaluate energy buffer capacitors using Nanolam capacitors, developed for use in inverters of hybrid and electric vehicles.  Nanolam capacitors comprise 10,000s of high temperature radiation cured polymers that have superior capacitance and dissipation factor stability in the temperature range of -196oC to +200oC.  Nanolam capacitors are self-healing, prismatic in shape and they are radiation tolerant.  One unique feature of the Nanolam capacitor technology is the use of submicron polymer dielectric layers.  It has been demonstrated that as the thickness of the cross-linked amorphous dielectrics decreases below about 1.0mm, the breakdown strength increases significantly, which results in capacitors with superior energy density.   Internal series sections allow Nanolam capacitors with dielectric thicknesses of few hundred nanometers to service applications with voltages as high as 10,000V. The proposed development will produce and evaluate energy buffer Nanolam capacitors with a rating of 1200mF/175VDC for an 120V power bus.  A single Nanolam capacitor will be used to replace at least ten individual MLC parts, mounted on a PCB to make up the 1200mF.  The major project objective is to demonstrate superior capacitance stability, energy density and specific energy to MLCs as well as deliver parts to the NASA technical personnel for independent evaluation.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Radioisotope dynamic power conversion systems controllers, as well as roll-out photovoltaic array controllers used to power Hall thrusters, are tailored mostly to 120V and there is some ongoing development with 300V systems.  Nanolam capacitors can replace multilayer ceramic capacitors in multiple circuits of a single controller.  Potential circuit applications include power factor correction in a rectifier circuit, energy buffer in an AC/DC inverter and DC-link in a DC/DC inverter.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Developing lower voltage capacitors will greatly expand the Nanolam market size and application space.  Non-NASA applications include inverters for residential and commercial PV systems, battery chargers, inverters for 48V automotive applications, used in soft hybrids as well as internal combustion vehicles with stop and go systems, and capacitors for commercial aviation and commercial satellites.

Duration: 6

PROPOSAL NUMBER:
 20-1- H8.01-6461
SUBTOPIC TITLE:
 Utilization of the International Space Station (ISS) to Foster Commercial Development of Low-Earth Orbit (LEO)
PROPOSAL TITLE:
 Biopharmaceutical Uniform Crystallization Test Bed
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Techshot, Inc.
7200 Highway 150
Greenville, IN 47124
(812) 923-9591

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Rachel Ormsby
E-mail:
rormsby@techshot.com
Address:
7200 Highway 150 Greenville, IN 47124 - 9515
Phone:
(812) 728-8122

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ms. Juanita Melton
E-mail:
jmelton@techshot.com
Address:
7200 Highway 150 Greenville, IN 47124 - 9515
Phone:
(812) 728-8135
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 6
Technical Abstract (Limit 2000 characters, approximately 200 words)

Pharmaceuticals in general, and biopharmaceuticals specifically, are often best formulated as microscopic crystals.  The crystalline state is most stable, allows a high-concentration, low-viscosity parenteral formulation, and facilitates alternate routes of administration. There is a requirement that the crystals be small, a few micrometers or less, and uniform, the same size within a few per cent.  The problem: most recombinant protein biopharmaceuticals do not crystallize uniformly.  A solution to this problem has been discovered in on-orbit crystallization experiments, which produced very uniform sized crystals. Manufacturers are creating demand for on-orbit testing of uniform crystallization protocols, but suitable hardware and ISS research opportunities are inadequate.  Techshot proposes a business plan in which cost and time saving versatile flight hardware and flexible flight opportunities are made openly available to corporate and institutional users seeking improvements or refinements in product purification, formulation and/or delivery.  Hardware and flight plans on ISS will be offered in which factorial and/or real-time photography experiments can be performed on the basis of Techshot’s regular ISS access and versatile hardware fleet.  In Phase I research Techshot will (1) adapt up to four different existing hardware modules for this specific application, (2) test these modules in model protein crystallization experiments in the laboratory, and (3) perform mathematical modeling for a ground-based crystallization reactor with adjustable parameters for approximating the relevant low-gravity physics.  In Phase II research Techshot will prepare the hardware modules for flight readiness, prepare an aggressive ISS use plan, and construct and operate an optimizable ground-based reactor.  The intended outcome is a business paradigm for hastening the availability of stable biopharmaceuticals with favorable options for delivery.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA has solicited research topics in this area of pharmaceutical production on spacecraft making deep space voyages to solve problems of availability and stowage.  Such projects include short-cut production of biopharmaceuticals by stored microbial cells but also need to include short-cut purification schemes.   A crystallization plan, Techshot’s proposed innovation, could eliminate several (chromatography, extraction, etc.) downstream steps toward such on-orbit formulation, although non-NASA commercialization is the project’s primary goal.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Success in producing a crystalline product will save big due to longer ambient stability, lower delivery volume and novel routes of administration of their product, whether it is an approved pharmaceutical or an emerging therapeutic. Techshot intends to offer crystallization research capabilities on the ISS and in labs to companies seeking opportunities in the crystalline biopharmaceutical field.

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.01-6606
SUBTOPIC TITLE:
 Lidar Remote Sensing Technologies
PROPOSAL TITLE:
 Femtosecond-Laser-Based Welding for the Fabrication and Integration of Lidar Lasers
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Aktiwave
241 Ashley Drive
Rochester, NY 14620
(585) 355-2706

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Pankaj Sahoo
E-mail:
psahoo@aktiwave.com
Address:
150 Lucius Gordon Drive Rochester, NY 14586
Phone:
(585) 355-2706

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Christopher Dorrer
E-mail:
cdorrer@aktiwave.com
Address:
241 ASHLEY DR ROCHESTER, NY 14620 - 3327
Phone:
(585) 355-2706
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

This proposal innovates an ultrafast laser welding (UFLW) system and processes that provide epoxy-free bonding of optical and mechanical components suitable for lidar sources in the space environment. This proposal responds to SBIR subtopic S1.01 Lidar Remote Sensing Technologies, aiming at improving instruments’ compactness, reliability, lifetime, and long-term performance. It will develop the UFLW technology from the theoretical and experimental standpoints with three objectives: (I) Theoretically investigate the physical mechanism of UFLW to predict weld geometry and thermal stress. (II)Experimentally investigate the impact of focusing conditions and inter-substrate gap height on weld geometry and bond strength. (III) Demonstrate effective UFLW of glass-to-glass/crystal and glass/crystal to metal. The simulations on ultrafast laser propagation, nonlinear absorption, plasma generation, heat accumulation, and melt zone formation will be conducted, predicting welding geometry. The effect of focusing conditions, scanning speed, and gap height on weld geometry and bond strength will be experimentally investigated. Optimum processing parameters for bonding the proposed glass/metal/crystal materials will be determined. Bond strength and weld geometry will be characterized and reported. UFLW will enable monolithic lasers and increase the integrity and durability of space-borne instruments. It will also benefit commercial sensors and advance very high Speed datacom & communications links via advanced electronics/photonics integration. The success of this project has high potential to enable the US to become the international leader of the emerging digital manufacturing sector enabled by ultrafast lasers. The offeror, Aktiwave LLC, is exceptionally well aligned with the goals and aspirations of the SBIR program, possessing leading expertise and capability in lasers and ultrafast-laser-based welding, polishing and structuring of optical materials.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Ultrafast laser welding of glass/crystal-to-metal is of special interest to NASA for fabrication of monolithic lasers as it eliminates epoxies, increasing the integrity and durability of space-borne instruments. It enables the integration electro-optical-mechanical components in small packages, reducing size, weight and power for resource-limited missions. NASA specific applications include lidar remote sensing, space flight instrument, device miniaturization and integration, elemental analysis and free-space communication.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Ultrafast-laser-based welding offers competitive advantages through direct bonding of optical, electrical and mechanical components for the following applications: spectroscopy, gas/chemical sensing, integrated photonic devices (functionality expansion and high-density packaging), medical industry (hermetic sealing of bio-implants), automotive industry, and electronics industry.

Duration: 6

PROPOSAL NUMBER:
 20-1- S2.02-6618
SUBTOPIC TITLE:
 Precision Deployable Optical Structures and Metrology
PROPOSAL TITLE:
 Thermally Stable Carbon Fiber 3D Printed Composite Tube Connectors for Low CTE Satellite Structures
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Mantis Composites
3986 Short Street, Suite 100
San Luis Obispo, CA 93401
(509) 737-7036

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Ryan Dunn
E-mail:
rdunn@mantiscomposites.com
Address:
3986 Short St, Suite 100 San Luis Obispo, CA 93401 - 7573
Phone:
(661) 769-6793

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. David Zilar
E-mail:
dzilar@mantiscomposites.com
Address:
3986 Short St, Suite 100 San Luis Obispo, CA 93401 - 7573
Phone:
(509) 737-7036
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

Imaging satellite structures require the highest possible thermal stability in order to maximize imaging precision. As the sizes of optics increase to accommodate ever-present inherent resolution limitations, these structures continue to grow with the expectation of similar or better overall thermal stability. These requirements spurred the development and maturation of low-CTE carbon fiber tube structures. While production of the carbon fiber tubes themselves is well developed to produce lightweight, low CTE structures, the components that attach these tubes are still heavy and expensive to produce.

 

Mantis Composites proposes a solution to this problem utilizing in-house-developed continuous 5-axis carbon fiber 3D printers. The 3D printing capability this provides allows for 3-dimensional fiber paths that can enable the low-CTE benefits of carbon fiber composites while retaining the intricacy capabilities of machined metals. With support of a prior $50,000 Air Force SBIR Phase I grant and matching funds from Ball Aerospace, we successfully produced a three-pronged ‘PVC style’ connector demonstrator with 90% weight reduction and improved mechanical performance over an equivalent Invar-36 component. We also developed and performed initial validation steps on a bonding system for our components to tube structures. This scope of work brought the effective TRL for this application of our manufacturing process to 3. 


The goal of this proposal is to utilize this same three-prong connector demonstration component to mature and develop applications specifically targeting low-CTE needs for applications such as optical benches and metering structures. During this Phase I, we will: validate, test, and modify existing bonding methods; validate predicted low-CTE results at a coupon level; adapt our three-prong connector design for low CTE filament by tuning processing parameters and fiber paths; and finally produce and mechanically test a full-scale tube and connector mock-up.

 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

While IR-band imaging systems (identified in the solicitation) are perhaps the most valuable application of the proposed capabilities, the component volumes are small. We also see significant applications in large space-based structures more broadly. NASA’s push for long distance human spaceflight will require large collapsible, lightweight structures. While less CTE driven, the other requirements this brings match with the proposed technology. We see low CTE structures as a convenient scope-limited qualification bridge to these applications. 
 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

From the National Reconnaissance Office to private LEO earth imaging companies, increasing the thermal stability of optical systems on is necessary to increase resolution. Since tube-and-beam structures are common between NASA and non-NASA optical systems, with metal components being the limiting weight and thermal stability factor for both, the proposed scope of work is equally applicable to both
 

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.11-6625
SUBTOPIC TITLE:
 In Situ Instruments/Technologies and Plume Sampling Systems for Ocean Worlds Life Detection
PROPOSAL TITLE:
 PWLSR - Pulsed Waveguide Latency Spectral Receptor
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Impossible Sensing, LLC
3407 South Jefferson Avenue
St. Louis, MO 63118
(314) 695-6993

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Pablo Sobron
E-mail:
psobron@seti.org
Address:
911 Washington Ave Ste 501 St. Louis, MO 63101 - 1243
Phone:
(314) 695-6993

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Pablo Sobron
E-mail:
psobron@seti.org
Address:
911 Washington Ave Ste 501 St. Louis, MO 63101 - 1243
Phone:
(314) 695-6993
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Whether using meltprobes, mechanical drills, or hybrid approaches, Europa ice penetration systems will likely utilize tether to provide data communication to the lander, and possibly power from it.  Our innovation, Pulsed Waveguide Latency Spectral Receptor, PWLSR, leverages such tethered approaches to ice penetration. Adding a single dispersive optical fiber cable, PWLSR turns the tether into a spectrometer that obtains time-correlated in-situ spectroscopy information aboard Europa iceprobes. PWLSR is a cost-effective way to enhance the science return of subsurface Europa missions: it adds just 2 kg and 2,000 cc to the iceprobe and a 0.2 mm fiber cable to the tether, and returns compositional information of the subsurface as the iceprobe advances through the ice.

PWLSR focuses laser light into the the ice, collects scattered and re-emitted photons, and launches them into a dispersive optical fiber integrated into the tether connecting iceprobe and lander. The fiber is terminated in a retroflector at the surface end of the tether which reflects light back into the fiber. Photons return to the iceprobe, where they are routed into a detector and analyzed. Results are compressed and transmitted to lander using tethered and/or free-space communication system.  PWLSR fiber cable can be split into several segments, linked by fiber-optic connectors. This way, it can be housed into several spool bays that can be sequentially left behind in the ice once a spool is depleted.

PWLSR combines, for the first time, deep subsurface access and laser spectroscopy to build a scientific instrument that addresses scientific objectives of future landed science missions to Ocean Worlds, particularly Europa.  Developing PWLSR is a key, risk-reducing effort that paves the way for maturation of the instrument towards flight while also stimulating technological innovation both for commercial and federal use beyond planetary exploration.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

PWLSR enables NASA's search for life by providing new sensing capabilities to Europa ice penetration platforms currently under development (e.g. SLUSH, Cryobot), which require instruments to be housed inside them.  PWLSR has potential to become a critical new instrument in NASA’s effort to detect evidence of life, especially extant life, in the ocean worlds of the outer solar system by providing in-situ analysis of subsurface ice and, if integrated with an ocean explorer, subsurface liquid water bodies as well.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The technology is directly applicable to deep ocean research (packed into ROV to perform laser spectroscopic sensing), resource exploration and development industries (in-situ downhole fluid analysis for the exploration and development of oil and gas and subsurface materials during exploration drilling in mining), and scientific end environmental drilling (environmental evaluation or remediation). 

Duration: 6

PROPOSAL NUMBER:
 20-1- H6.04-5136
SUBTOPIC TITLE:
 Model Based Systems Engineering for Distributed Development
PROPOSAL TITLE:
 Stakeholder Access to Embedded System Models (SAESM)
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Adventium Enterprises, LLC
111 Third Avenue South, Suite 100
Minneapolis, MN 55401
(612) 280-9843

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Rand Whillock
E-mail:
rand.whillock@adventiumlabs.com
Address:
111 Third Avenue South, Suite 100 Minneapolis, MN 55401 - 2551
Phone:
(612) 567-2631

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Kyle Nelson
E-mail:
kyle.nelson@adventiumlabs.com
Address:
111 Third Avenue South, Suite 100 Minneapolis, MN 55401 - 2551
Phone:
(612) 280-9843
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

The Stakeholder Access to Embedded System Models (SAESM)  project will produce a vendor neutral model-based systems engineering (MBSE)  analysis environment that supports Consultative Committee for Space Data Systems (CCSDS) Spacecraft Onboard Interface Services standard Electronic Data Sheet (SEDS) generation from existing models, e.g., models written in System Modeling Language (SysML), Future Airborne Capability Environment (FACE), and Architecture Analysis and Design Language (AADL),  ingestion of existing SEDS into the environment, and virtual integration of the systemrepresented in the environment.  Virtual integration is a process of analyzing detailed models of embedded software systems to uncover errors primarily related to non-functional requirements, including timing, safety, and security.  These errors are generally not uncovered until integration and test phases when costs to fix them are prohibitive. SAESM will enable multiple stakeholders to conduct these analyses without requiring expert knowledge of the underlying modeling language(s).  SAESM supports vendors by enabling them to support NASA’s SEDS initiative using modeling languages they are already using, supports NASA personnel by automatically creating and maintaining SEDS, and supports all parties with virtual integration. This improves system capability by reducing risk of cost and schedule overruns due to late discovery of errors.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The NASA markets are mission-critical cyber-physical system (CPS) with significant functionality captured in software. NASA programs that would benefit include the Lunar Gateway, Artemis, Human Landing System, the Europa Clipper, X-57 Maxwell electric aircraft, and other next generation vehicle developments. 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The non-NASA applications are those with systems that are analogous to those in the NASA market, examples include Department of Defense, aerospace, automotive, and industrial markets. In addition, analogous international markets are also available.

Duration: 6

PROPOSAL NUMBER:
 20-1- S2.03-5102
SUBTOPIC TITLE:
 Advanced Optical Systems and Fabrication/Testing/Control Technologies for EUV/Optical and IR Telescope
PROPOSAL TITLE:
 Beyond Resolution Reconstruction of Surface Metrology Data
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
HighRI Optics
5401 Broadway Terrace #304
Oakland, CA 94618
(800) 470-7902

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Keiko Munechika
E-mail:
km@highrioptics.com
Address:
5401 Broadway Terr #304 Oakland, CA 94618 - 1767
Phone:
(360) 402-4112

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Keiko Munechika
E-mail:
km@highrioptics.com
Address:
5401 Broadway Terr #304 Oakland, CA 94618 - 1767
Phone:
(360) 402-4112
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

The performance of any metrology tool, and the level of confidence in the data obtained, directly depends on the ability to characterize (calibrate) the tool, enabling data processing to mitigate the effects of imperfections of the tool. However, there is no commonly accepted method to characterize the performance of metrology tools or calibrate them with high accuracy. Such characterization is a difficult task; the quality of the measured image (topography) data depends on both the tool itself and the experimental setup, and the interpretation of the results is often subjective and incomplete.

We propose to develop a robust methodology and technology to quantitatively characterize metrology instrumentations, and create the first reliable and commercial solution for beyond-resolution reconstruction of 2D surface topology data. The technology will increase the spatial resolution of the metrology data needed for fabrication and optimal usage of the existing optical components in x-ray optical systems, performance simulation of new x-ray space telescopes, and x-ray beamlines under development.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The first reliable and commercial solution for 2D data reconstruction will provide one of only a few technologies for increasing the spatial resolution of the metrology data needed for fabrication and optimal usage of the optical components in x-ray optical systems and sophisticated performance simulation of new x-ray space telescopes and x-ray beamlines under development for the NASA space missions. 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The final commercial product will improve the metrology tool’s performance via sophisticated beyond-resolution reconstruction of the metrology data. As a result, this product will bring existing metrological tools to their highest possible performance level; it will also enable faster improvements in future designs of the instrumentation by equipment manufacturers.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z1.03-5319
SUBTOPIC TITLE:
 Kilowatt-Class Energy Conversion for Small Fission Reactors
PROPOSAL TITLE:
 Kilowatt Class Fission Energy Conversion
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
QorTek, Inc.
5933 North Route 220 Highway
Linden, PA 17744
(570) 322-2700

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Ross Bird
E-mail:
rbird@qortek.com
Address:
5933 N Route 220 Hwy Linden, PA 17744 - 7703
Phone:
(570) 322-2700

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Zachary Stimely
E-mail:
zstimely@qortek.com
Address:
5933 N Route 220 Hwy Linden, PA 17744 - 7703
Phone:
(570) 322-2700
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

NASA’s Kilopower program aims to jumpstart a new approach to powering exploration in the future by utilization of fission reactors.  The heat from these reactors then drives Stirling engines that when coupled with generators, can produce the power required for future missions.  The proposed program aims to have QorTek work with Sunpower to further enhance the capability of their Stirling generators and provide a radiation hardened solution for NASA’s program requirements.  Previous work completed by Sunpower has demonstrated the operation of the engine and controller and to meet this program’s requirements will require the current generation of Stirling controller to be upgraded to 1kW of capability.  The design of the controller and Stirling engine is desired to be modular such that multiple 1kW systems can be placed in parallel further increasing power availability.  With the design completed and with engine simulators from Sunpower, we aim to demonstrate the feasibility and operation of the engine before focusing on core components to radiation hardened.  Radiation hardening is anticipated to be a challenge due to the proximity of the engine and controller electronics to the reactor and the objective is to utilize state of the art WBG materials to help achieve as high a radiation resistance as possible to minimize required shielding. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

A critical application for this technology is with NASA’s current Kilopower program and firstly, demonstrating a full system at the 1kW level.  The Titan Saturn System Mission (TSSM) is now considering employing a 1KW version of Kilopower design if it comes to fruition. This mission will include both Titan orbital flybys and lander. Another potential Kilopower insertion mission would be the Kuiper Belt Object Orbiter (KBOO).

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Non-NASA applications for this technology would potential be focused on our Navy and Army programs.  In addition, the Air Force and MDA would have interest in the converters and the Rad hard technology.  Both DoD entities have interest in radiation hardened designs and the challenge of this program, specifically dealing with neutrons will lend itself well into these government agency programs.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z1.05-5373
SUBTOPIC TITLE:
 Lunar & Planetary Surface Power Management & Distribution
PROPOSAL TITLE:
 High Dielectric Strength Thermally Stable Wire Insulation
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Trimer Technologies, LLC
3905 Varsity Drive
Ann Arbor, MI 48108
(480) 205-1202

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Megan Dunn
E-mail:
Dunn@trimerllc.com
Address:
3905 Varsity Drive Ann Arbor, MI 48108 - 2225
Phone:
(480) 205-1202

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Henry Sodano
E-mail:
hsodano@trimerllc.com
Address:
3905 Varsity Dr. Ann Arbor, MI 48108 - 2225
Phone:
(480) 205-1202
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

NASA’s Global Exploration Roadmap and the Space Policy Directive detail NASA’s plans for future human-rated space missions and the need for power distribution to bases on the lunar surface and eventually Mars.  In order to enable high power (>100kW) and longer distribution systems on the surface of the moon or Mars, NASA is in need of low mass insulating materials which offer greater dielectric strength and operate in extreme temperature environments.  Wires are often coated with a thin layer of acrylic, polyurethane, polyester imide or polyamide imide to provide insulation and allow them to operate at high voltage, however these materials cannot withstand the high temperatures required for space applications.  When thermal stability is required, polyimides or fluorinated polymers such as PTFE are used, however these materials are costly, difficult to coat and in the case of fluorinated polymers exhibit poor adhesion to the wire.  The proposed SBIR will develop a thermosetting resin that offers low cost, high glass transition temperature, excellent adhesion to metallic substrates and greatly improved dielectric strength over currently used enamels.  Furthermore, the resin has a low processing viscosity which can allow thin insulation layers and can be cured in seconds, therefore, enabling rapid manufacture of lighter weight wire that can withstand extreme temperatures.  While current high Tg resins cost hundreds of dollars per pound, Trimer’s resin can be produced for dollars a pound.  In addition to the low cost, which is not the primary driver for aerospace materials, Trimer’s material exhibits excellent processability and mechanical properties and was recently measured to have a dielectric strength over 760 MV/m which is more than double polyimides.  Ultimately, the proposed polymer has the potential to drastically reduce the cost of magnet wire and produced thermally stable coatings which can be applied for future human-rated space missions.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Throughout NASA’s technology roadmap the need for improved materials is called out in nearly all Technology Areas and are highlighted as the enablers behind the systems that NASA develops and uses to fulfill its missions.  This need is evident throughout the next-generation space missions, which require insulators with greater dielectric strength and thermally stability for the wiring used in power transmission as well as motors, high voltage electronics and the encapsulation of electrical components.  

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The market for electromagnetic systems is experiencing significant growth, driven by electric vehicles and wind power as well as increasing wealth in emerging economies. Our commercialization efforts will seek to capitalize upon the low cost to produce polymers with high thermal stability and dielectric strength to market the resin in a range of industrial power applications.  

Duration: 6

PROPOSAL NUMBER:
 20-1- Z10.03-5512
SUBTOPIC TITLE:
 Nuclear Thermal Propulsion
PROPOSAL TITLE:
 (U,Zr)C Mixed Carbide Fuel Coatings Using Impulse PVD
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Starfire Industries LLC
2109 South Oak Street
Champaign, IL 61820
(708) 955-6691

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Brian Jurczyk
E-mail:
bjurczyk@starfireindustries.com
Address:
2109 South Oak Street Champaign, IL 61820 - 0905
Phone:
(708) 955-6691

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Brian Jurczyk
E-mail:
bjurczyk@starfireindustries.com
Address:
2109 South Oak Street Champaign, IL 61820 - 0905
Phone:
(708) 955-6691
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

NTP has multiple goals ranging from higher exhaust temperature (>1000s Isp), hot corrosion resistance (diverse propellants: H2, CH4, NH3, H2O), higher power density (thrust, >5MW/L goal), local fission product retention (materials damage, migration), manufacturability (cost, materials), safety (ground testing, flight), long core lifetime for interplanetary round trips (single fuel load, good burnup, control, 5+ years), and commonality with terrestrial applications (SMR, MNR, industrial heat, DoD/Pele) and advanced applications like reusable hypersonics, Luna/Mars surface power). 

A solution, called the Coated Mixed Carbide (CMC) fuel element approach, is a hybrid between distributed solid-solution carbides from the Rover/NERVA days and localized TRISO fuel from today’s small modular reactor concepts.  Very high temperature ~3500K (U,Zr)C fuel is concentrated in small kernels and protected against attack by hydrogen from outside and from fission products within by engineered multilayered coatings.  An recent innovation in high-power impulse magnetron sputtering (i.e. IMPULSE® + Positive Kick™) allows conformal coatings of the small-diameter fuel kernels with ‘TRIZO-like’ protective layers to enable high-power density NTP reactors.  With precision ion energy and deposition flux control, each multilayer can be engineered for specific property, such as fission gas retention, compressive stress, hydrogen permeability, ductility, etc. These 'TRIZO-like' pellets are embedded in a ZrC(W) matrix and distributed for lower peaking factor across the fuel element.  Embedded propellant channels can be used for direct nuclear thermal propulsion or bimodal heat pipe power extraction for electrical power generation.

This Phase I SBIR builds on three patent-pending technologies and seeks to demonstrate feasibility of the concept, identity and rank technical risks and prioritize investment in Phase II towards retiring the necessary risks.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)
  • NTP Flight Demonstration Project
  • Lunar Power Station Demo
  • NASA Robotic Science Missions To Outer Solar System
  • Long-Life, Reusable Bi-Modal Propulsion and Power For Crewed Mars
  • Mars Power Station Demo
  • Beyond Solar System Exploration
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)
  • Commercial Microreactor Electrical Power Systems <25MW
  • DoD/Army Forward Basing Electrical Power (Project Pele)
  • DoD/Navy Directed Energy Power Upgrades
  • DoD/DARPA Reusable Hypersonic Vehicles
  • Industrial Process Heat
Duration: 6

PROPOSAL NUMBER:
 20-1- S5.01-5983
SUBTOPIC TITLE:
 Technologies for Large-Scale Numerical Simulation
PROPOSAL TITLE:
 Ecosystem for Early Feedback-Driven HEC Code Development
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
RNET Technologies, Inc.
240 West Elmwood Drive, Suite 2010
Dayton, OH 45459
(937) 433-2886

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Gerald Sabin
E-mail:
GSabin@RNET-Tech.com
Address:
240 West Elmwood Drive, Suite 2010 Dayton, OH 45459 - 4248
Phone:
(937) 433-2886

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
V Nagarjan
E-mail:
vnagarajan@rnet-tech.com
Address:
240 West Elmwood Drive, Suite 2010 Dayton, OH 45459 - 4248
Phone:
(937) 433-2886
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

PerfDev is an intuitive, full featured and collaborative automated optimization and code analysis framework that promotes and enables on-the-fly performance optimization of advanced scientific applications to maximize code development and application efficiency.

 

The PerfDev software development and optimization framework enables stateful runtime decomposition and passive exploration of code blocks. PerfDev will enable advanced parameter space exploration using deep learning. Instead of waiting to evaluate application performance at the end of a full development cycle, PerfDev will enable real-time performance feedback loops that facilitate the optimization of individual blocks of code as the application is developed or ported. The production PerfDev APIs will be integrated into multiple production environments (starting with Jupyter in Phase I), will support a range of performance metric tools and hardware (e.g., PAPI/perfcntr, SONAR, Caliper, etc.), and multiple compute languages (e.g., C/C++, Fortran, Python).

 

Towards that goal, and in an effort to demonstrate the importance, feasibility and usability of the proposed framework, the Phase I effort will focus of the following  objectives in order to develop a functional PerfDev prototype:

  • Code Cell Identification and Automatic Modularization for NASA Applications: Defining application "code cells" is a key component to enable a PerfDev optimization analysis. The code cells are the fundamental unit of evaluation and analysis.
  • Distributed PerfDev Checkpoint-Restart: Checkpoint-restart is a fundamental utility that enables the efficient execution and evaluation of system and application parameters during code development. During Phase I, we will integrate support for MPI-supported application level checkpointing into our C/C++ backend in the PerfDev prototype.
  • PerfDev API for Automation Parameter Space Exploration: We will develop an API to enable passive automatic parameter space exploration of code cells.
Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The PerfDev framework will be beneficial for optimization of HEC/HPC NASA applications that are being developed in C, C++, Fortran, Python and Perl. The tool will aid NASA while developing new applications and porting/optimizing existing applications for new and complex compute architectures.

Software of potential interest to NASA include CFD, CSD, FEM, and other numeric simulation applications and libraries. PerfDev will also lead to an improved software development lifecycle that better meets the current high performance computing environment.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Many government agencies, university research groups, and industry researchers are utilizing high performance computing systems and face the same challenges in developing and optimizing codes for new and existing architectures. All of these sectors need an adequate tool to help in optimizing and porting applications to emerging high performing compute systems.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z3.05-6476
SUBTOPIC TITLE:
 Satellite Servicing Technologies
PROPOSAL TITLE:
 An Additively Manufactured, Leak-Proof NTO Swivel
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
ASRC Federal Astronautics, LLC
289 Dunlop Boulevard, Building 300
Huntsville, AL 35824
(256) 679-9189

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Joseph Sims
E-mail:
jsims@QuadrusCorp.com
Address:
289 Dunlop Blvd., Bldg. 300 Huntsville, AL 35824 - 1122
Phone:
(256) 801-3128

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Joseph Sims
E-mail:
jsims@QuadrusCorp.com
Address:
289 Dunlop Blvd., Bldg. 300 Huntsville, AL 35824 - 1122
Phone:
(256) 801-3128
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

ASRC Federal Astronautics, LLC (AFA) is pleased to present this proposal for the demonstration of feasibility of an additively manufactured, highly dexterous mechanism that enables the safe, leak-free transfer of the storable oxidizer (nitrogen tetroxide, NTO, or mixed oxides of nitrogen, MON). Our Additively manufactured Dexterous Leak-proof Interface (ADLI) is a radically simple design that uses three additively manufactured (AM) parts configured to interface with just a few commercial off-the-shelf (COTS) components.  Importantly, our design uses no seals and no soft goods, yet still interfaces with propellant service valves along any vector within a full hemisphere about the hinge for the pitch axis. In short, ADLI provides the flexibility to transfer propellant from a servicing satellite, which is in a huge range of orientations relative to a dead satellite with virtually any propellant service valve configuration.

ADLI exhibits several features that bring benefits to future satellite servicing missions: 

  1. ADLI will meet or exceed the leak requirement of 1x10-5 standard cm3 per second of gaseous helium.
  2. ADLI has two joints thatare actuated separately, so the outlet can be normally-oriented to any point on a hemisphere situated about the pitch axis, which provides enormous flexibility for orienting the servicing spacecraft and for interfacing with the spacecraft being serviced.
  3. ADLI uses metal AM for manufacturing the basic fluid bulkheads, any number and diameter of inlet and outlet tubes can be bought and used, which means a wide range of flowrates and pressure drops can be accommodated to meet mission requirements.
  4. ADLI’s service life will be far in excess of 10 cycles, which helps enhance the profitability and the return on investment for satellite servicing companies.
  5. Because we use Ti-6-4 and Nitinol for the primary components, ADLI should be highly compatible with NTO, which our Phase I project will confirm.
Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NTO transfer interface for satellite servicing missions

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

NTO transfer interface for satellite servicing missions

Duration: 6

PROPOSAL NUMBER:
 20-1- Z8.09-6240
SUBTOPIC TITLE:
 Small Launcher Lunar Transfer Stage Development
PROPOSAL TITLE:
 High Impulse Electric Upper Stage for Small Launch Vehicles
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Busek Company, Inc.
11 Tech Circle
Natick, MA 01760
(508) 655-5565

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
James Szabo
E-mail:
jszabo@busek.com
Address:
11 Tech Circle Natick, MA 01760 - 1023
Phone:
(508) 655-5565

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Judy Budny
E-mail:
judy@busek.com
Address:
11 Tech Circle Natick, MA 01760 - 1023
Phone:
(508) 655-5565
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Busek Co. Inc. proposes to develop a high total impulse electric upper stage for small launch vehicles.  The stage will be propelled by Busek’s 600 W Hall thruster. With xenon, which is the baseline propellant, the nominal specific impulse is 1500 s. The thruster may also be fueled by low cost krypton or high density iodine.  Power will be provided by solar arrays.  Total impulse will be sufficient to move a payload from low Earth orbit (LEO) to low Lunar orbit (LLO).

In Phase I, Busek will work with NASA and launch vehicle suppliers to design the upper stage.  Phase I will include a Preliminary Design Review (PDR) level design for a flight-like system and a near-Completion Design Review (CDR) level design for the prototype system.  The phase 1 report will include a mapping of key performance parameters (mass, power, cost, etc.) from the prototype to the flight design, along with potential opportunities for technology demonstration and commercialization. 

In Phase II, the design of the stage will be completed, and key elements of the prototype propulsion system will be fabricated and tested. The thruster will undergo delta-qualification testing as required.  At the end of Phase II, Busek will deliver key elements of an integrated prototype propulsion system that could be ground or flight tested as part of a post-Phase II effort.  These will include, at minimum, a thruster and discharge power converter.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The target NASA application is a high delta-V upper stage for commercial launch vehicles. NASA is interested in the development of a low cost cis-lunar transfer stage to guide and propel small spacecraft on Trans Lunar Injection (TLI) trajectories that will enable the spacecraft to enter lunar locations or orbits.  NASA can also use the propulsion system for Earth orbiting or interplanetary spacecraft of all sizes.  Exploration, earth science, planetary science, astrophysics and heliophysics science all benefit from electric propulsion (EP).

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The upper stage can also be used for DoD and commercial launches, including LEO to GEO transfers for small spacecraft.  General applications for HETs include orbit raising and lowering, drag compensation, changing orbit inclination and phase, orbit maintenance (including North-South station-keeping, East-West station-keeping in GEO, and a deorbiting a spacecraft at end-of-life.

Duration: 6

PROPOSAL NUMBER:
 20-1- A3.02-5310
SUBTOPIC TITLE:
 Increasing Autonomy in the National Airspace System (NAS)
PROPOSAL TITLE:
 Gaining Actionable Insights Through Neurocomputational Trajectory Segmentation and Clustering
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Intelligent Automation, Inc.
15400 Calhoun Drive, Suite 190
Rockville, MD 20855
(301) 294-5221

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Alexander Grushin
E-mail:
agrushin@i-a-i.com
Address:
15400 Calhoun Drive, Suite 190 Rockville, MD 20855 - 2814
Phone:
(301) 294-5224

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mark James
E-mail:
mjames@i-a-i.com
Address:
15400 Calhoun Drive, Suite 190 Rockville, MD 20855 - 2814
Phone:
(301) 294-5221
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

The key innovation of this project is the development of a NEurocomputational Trajectory Segmentation and Clustering (NETS) tool that will apply segmentation, explainable clustering, and unsupervised machine learning algorithms to gain actionable insights from large volumes of aircraft trajectory data. National Airspace System (NAS) trajectory data has all the characteristics of “Big Data” such as volume, velocity, variety, and veracity and is widely available through services such as the System Wide Information and Management System (SWIM). Increased demand on the NAS and greater availability of data requires new tools and techniques to be developed to take full advantage of all available trajectory data. For this effort, Intelligent Automation, Inc. will develop the NETS tool to mine large volumes of trajectory data in order to gain actionable insights with the goals of improving aviation safety and efficiency, identifying anomalous and emergent behavior, and studying the impact of new entrants such as space vehicles, unmanned aircraft systems, and urban air mobility vehicles. Our NETS solution will apply state-of-the-art neurocomputational algorithms to partition a trajectory into meaningful segments and then group similar segments into clusters, thus enabling the automatic discovery of common, anomalous, or emergent movement patterns. The segmentation process ensures that meaningful trajectory segments are not missed, which could occur if a trajectory is considered as a whole. The NETS approach enables trajectories to be segmented and clustered in an unsupervised manner. Labels can then be assigned by a domain expert to each cluster to provide a classification. An explanation or rationale for why a trajectory segment was placed into a particular cluster will be provided by the NETS tool in order to facilitate the labeling process.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Our NETS solution, which involves neurocomputational algorithms and knowledge discovery, can provide complementary functionality to any NAS data analytics suite such as NASA’s Sherlock and the FAA’s Big DAWG analytics. NETS will allow researchers, analysts, and engineers to mine large volumes of trajectory data in order to gain actionable insights with the goals of improving aviation safety and efficiency, identifying anomalous and emergent behavior, and studying the impact of new entrants.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Aircraft operators such as passenger airlines, cargo airlines, UAS, UAM, and business jet operators can use NETS as part of a post-operations analytics suite used to analyze and improve operations.  NETS reporting of discovered movement patterns can be made to both users and to automated systems, in order to perform downstream tasks such as prediction and prognostics.

Duration: 6

PROPOSAL NUMBER:
 20-1- H4.01-5892
SUBTOPIC TITLE:
 Exploration Portable Life Support System Component Challenges
PROPOSAL TITLE:
 Vacuum-Regenerable Sorbent for NASA’s Exploration Portable Life Support System
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
XploSafe, LLC
712 Eastgate Street
Stillwater, OK 74074
(918) 813-2955

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Evgueni Kadossov
E-mail:
evgueni@xplosafe.com
Address:
712 Eastgate Street Stillwater, OK 74074 - 6409
Phone:
(405) 334-5720

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Shoaib Shaikh
E-mail:
shoaib@xplosafe.com
Address:
712 S Eastgate Street Stillwater, OK 74074 - 6409
Phone:
(918) 813-2955
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

In this Phase I SBIR, XploSafe proposes to develop and confirm the  technical feasibility of the use of nanoporous silica as a vacuum regenerable sorbent for integration into NASA’s Exploration Portable Life Support System (xPLSS). Not only is this sorbent vacuum regenerable, it has other advantages over activated carbon that could benefit the NASA space program. Two of these is higher sorption capacities for volatile organic compounds and more rapid sorption rates that could lead to reduced weight and size requirements. In this investigation, the sorption rate and capacity for seven of the highest priority trace contaminants (based on generation rates and Spacecraft Maximum Allowable Concentrations (SMAC) limits) will be determined. The ability for these contaminants to be removed from the sorbent by exposure to a moderate vacuum at ambient temperature will be demonstrated. Once the uptake capacities and rates for each trace contaminant are known for the OSU-6  sorbent and the logistics for vacuum regeneration of the sorbent have been determined, it will be possible to create a concept design for the vacuum regenerable element that could be integrated into the Exploration Portable Life Support System. This will be used in Phase II to produce and test a prototype vacuum-regenerable Trace Contaminant Control element

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Successful development of the proposed technology will advance the state of the art in trace contamination control. As a part of the Exploration Portable Life Support System (xPLSS) and the Exploration Extra-vehicular Mobility Unit (xEMU) units, the platform technology will advance the viability of NASA's crewed deep space exploration objectives.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Success in developing more effective and efficient filtration media could provide a significant enhancement in the protection of public health and the environment. This new filter media will serve a wide variety of markets as high efficiency particulate air filters (HEPA) in HVAC systems. Applications range from clean rooms, labs, industrial manufacturers, coal and ore mining facilities etc.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z13.02-6403
SUBTOPIC TITLE:
 Dust Tolerant Mechanisms
PROPOSAL TITLE:
 Dust Tolerant Joints
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Triton Systems, Inc.
200 Turnpike Road
Chelmsford, MA 01824
(978) 250-4200

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Jennifer Smith
E-mail:
jsmith@tritonsys.com
Address:
200 Turnpike Road Chelmsford, MA 01824 - 4040
Phone:
(978) 856-4188

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Collette Jolliffe
E-mail:
cjolliffe@tritonsystems.com
Address:
200 Turnpike Road Chelmsford, MA 01824 - 4040
Phone:
(978) 856-4158
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Lunar explorations have identified significant lunar dust-related problems that will challenge future mission success. Mechanical systems will be exposed to harsh regolith dust that comprises particles ranging in size from tens of nanometers to microns, and they need to operate on the dusty surface of the moon for months to years with little to no maintenance. NASA seeks technologies in rotary, linear and static joints that will protect from or tolerate dust intrusion. For this Phase I project, Triton will leverage our extensive experience in developing innovative bearings solutions for contaminant-rich environments to design and fabricate dust tolerant joints. We will perform environmental ultra-fine dust tests on the prototypes and evaluate their ability to mitigate and tolerate dust. A report detailing the design concepts and test results, along with recommendations on methods to optimize their performance will be delivered. In Phase II, Triton will optimize joint designs to mitigate dust, fabricate and test the prototypes under simulated operational conditions. Phase II deliverables will include a functional prototype, test results, as well as technology maturation and transition plan for application to mission-worthy systems.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

This proposed program will deliver dust tolerant joints that will protect from or tolerate dust intrusion. The novel technology will enable mechanical systems to operate on the dusty surface of the moon for months to years, thus extending their lifetime and enabling the success of future lunar explorations. The dust tolerant joints can be used for Life Support Systems, Advanced Extra Vehicular Activity Systems, Space Suit Assembly, Robotics and Mobility Systems and In situ Resource Utilization.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

This program will deliver a platform technology for mitigating dust in joints. Due to the ubiquity of joints in mechanical systems, this technology will extend the lifetime of mechanical systems used in contaminant-rich environments, leading to improved efficiency and cost savings. It will benefit numerous industries, including aerospace, automotive, heavy machinery, renewable energy, agriculture.

Duration: 6

PROPOSAL NUMBER:
 20-1- H10.01-4866
SUBTOPIC TITLE:
 Advanced Propulsion Systems Ground Test Technology
PROPOSAL TITLE:
 Composite Facility Components
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Gloyer-Taylor Laboratories, LLC
112 Mitchell Boulevard
Tullahoma, TN 37388
(931) 455-7333

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Eric Jacob
E-mail:
eric.jacob@gtlcompany.com
Address:
112 Mitchell Boulevard Tullahoma, TN 37388 - 4002
Phone:
(931) 455-7333

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Paul Gloyer
E-mail:
paul.gloyer@gtlcompany.com
Address:
112 Mitchell Boulevard Tullahoma, TN 37388 - 4002
Phone:
(931) 455-7333
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

 

For over 10 years GTL has been developing novel rocket system components. Originally funded by DARPA, with additional funding by NASA, GTL has developed a novel composite system (BHL™) for cryogen storage and transfer. BHL is used to produce LOX and cryogen compatible components that leverage the full strength of carbon fiber. For ground systems, the reduction in thermal mass will be more advantageous than the mass reduction (1/4 the mass of existing state of the art equivalents). BHL has 5-7 times lower thermal mass than stainless steel components, and over 10 times lower thermal mass than aluminum components (for the same pressure capability). BHL tubes chill down in less than 10% of the time of stainless-steel tubes. This increases the quality of the cryogenic liquid, reduces bubble entrainment, and allows for longer tube run lengths.

Composite structures are insensitive to hydrogen embrittlement and are highly resistant to fatigue. Furthermore, composite structures CTE can be tailored allowing for a zero lengthwise CTE. This ensures that components will not move around, fighting connection points and interconnections, further reducing fatigue and failure mechanisms.

In addition to the nominal benefits, GTL has developed a novel flow sensor method based around BHL. This sensor will allow for monitoring of the flow velocity profile, quality, and fill level.

In this phase I effort, GTL will design and produce a series of test articles to demonstrate the application of BHL to ground systems. This includes the extension to very high pressures, ground handling damage testing, and flow sensor testing. GTL is experienced in cryogenic testing, LOX and LCH4 testing, propulsion system design and testing, and ground facility production. In the phase II, full scale components will be produced and delivered, and testing can be performed yielding a high-quality validation data set for TRL advancement.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Low thermal mass, low mass cryogenic compatible components and sensors are applicable to many of NASA systems including ground test facilities, launch vehicles, nuclear propulsion, landers, lunar and mars habitats, and other space systems. The significant reduction in mass of cryogenic storage and transfer from BHL will allow for the highest performing cryogen systems ever produced.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The DoD and commercial launch services will benefit greatly from BHL components. Similar to the benefits for NASA, the low mass, low thermal mass properties, among others, are very beneficial to nearly all space systems. BHL components will also be useful for commercial cryogenic ground systems to reduce boil-off and chill-down time.

Duration: 6

PROPOSAL NUMBER:
 20-1- S5.06-5636
SUBTOPIC TITLE:
 Space Weather R2O/O2R Technology Development
PROPOSAL TITLE:
 Space-Weather CubeSat Array for 24/7 Prompt Global Coverage Experiment (SWAP-E)
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
NearSpace Launch, Inc.
8702 East 825 South
Upland, IN 46989
(765) 998-8942

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Henry Voss
E-mail:
hankvoss@nearspacelaunch.com
Address:
8702 E. 825 S. Upland, IN 46989 - 9765
Phone:
(765) 618-3813

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Matthew Voss
E-mail:
mattvoss@nearspacelaunch.com
Address:
8702 E. 825 S. Upland, IN 46989 - 9765
Phone:
(765) 618-3814
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

This proposal addresses Strategic Action Plan specifically for S5.06 SBIR area: Space Weather Instrumentation. A Space Weather (SW) array of 4 CubeSats released from a standard 6U deployer are each linked through the Globalstar constellation (much capacity) to provide near real-time ionospheric forecasting. Each CubeSat provides low-latency connections via space-space links in a redundant, time-ordered and common database (O2R) for prompt 24/7 data with a latency of seconds.

              The proposed Phase 1 study looks at providing instrumentation for analytic model validation that includes several proven SW instruments:  energetic particle detector, plasma probe, an IR cooled grid imager, a magnetometer, and GPS.   Each of the 4 CubeSat strings include four 20cm solar/plasma foldouts that separate the relatively noisy ThinSat Bus section from the quiet and cooled ThinSat Payload section to improve sensor performance. The 6U array of 4 CubeSats would be staggered in orbit via drag variations to give pole-to-pole orbit data every 12 minutes on average and in situ drag data at affordable cost in the 100 to 700 km orbit region. Prompt and Multipoint SW sensors would improve rapid forecasting and understanding new energy transfer with the goal to deliver end-user action (2018 Space Weather Phase 1 Benchmarks Report from the Presidents National Science and Technology Council).

 

Feasibility: NSL has recently successfully flown the first 60 CubeSat (ThinSats) array with articulating foldouts, particle detectors, IMU, IR imager, and Globalstar links as a demonstration project released from an NG-11 rocket to the ISS on April 17, 2019 (SSC19-S2-08, 2019).  NSLhas 400 subsystems in orbit with 100% success and currently delivering 10 CubeSats for launch in 2020.  The six Phase 1 results include: 1) Requirements, 2) SW Sensor Trade-Space matrix, 3) Existing Bus revisions, 4) Functional Prototype, 5) Balloon Flight of one CubeSat string (TRL=6), and 6) Final Report.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)
  1. Will provide new data driven operational forecasting tools to validate models
  2. Will pioneer a new spacecraft architecture with ThinSat  “strings” or “trains”  
  3. Will provide radiation environment to improve aircraft safety.
  4. Underexplored Sun-Earth coupling region explored between 100 to 350 km
  5. Forecasting Atmospheric drag with direct measurements above 100km.
  6. Study reentry region above 100km  
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

1.   Potential blackout impulses (large Solar Flare energetic particles, geomagnetic storms, meteors, or an EMP pulse).  SWAP-E will add new Prompt real time data and critical mapping. 
2.    SWAP-E ThinSat Sat array concept ideal for Lunar orbit and planetary experiments
3.    Advanced Manufacture of ThinSat “String or Trains” consisting of a stiff solar array foldout is a new architecture

Duration: 6

PROPOSAL NUMBER:
 20-1- H9.07-6104
SUBTOPIC TITLE:
 Cognitive Communication
PROPOSAL TITLE:
 Spiking Neuromorphic Software Defined Networking
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Brisk Computing, LLC
1191 Red Ash Court
Centerville, OH 45458
(937) 765-7742

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Chris Yakopcic
E-mail:
cyakopcic@gmail.com
Address:
1191 Red Ash Ct Centerville, OH 45458 - 4763
Phone:
(412) 916-7825

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Tarek Taha
E-mail:
ttaha@ieee.org
Address:
1191 Red Ash Ct Centerville, OH 45458 - 4763
Phone:
(937) 765-7742
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

The provision of high performing and efficient data communications is crucial for the success of most space exploration missions. Many challenges affect this goal as data transmissions have to occur over unreliable channels that span very large distances and that may not be available continuously over time. As a result, communication opportunities must be exploited optimally to achieve the reliable, high volume and low latency data transfers that will be demanded by future space missions. 

This goal is hindered by the use of a communication management approach that is mainly centralized. Such practice creates limitations to what can be optimized not only because of the need for expert human assistance but also because certain system updates could not be communicated to the required network devices within a reasonable time to be effective given the physical dimensions and nature of the network.

We propose to develop a software-defined networking method that exploits cognitive networking methods to optimize the transmission of data flows in a space network. We propose to utilize the Intel Loihi spiking neural network processor and develop learning algorithms for it to achieve very low SWaP processing. The key benefit of this approach will be novel scheduling capabilities that are also implemented on an ultra low SWaP system, making it very suitable for power constrained systems, such as cubesats. This work is being carried out jointly with the University of Houston.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Potential NASA applications include cognitive networking systems for satellites, in particular for constellations of satellites. 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Potential non-NASA applications include terrestrial software defined radio communications systems, particularly for systems that are deployed remotely and need high performance communications but low power consumption.

Duration: 6

PROPOSAL NUMBER:
 20-1- S2.04-6117
SUBTOPIC TITLE:
 X-Ray Mirror Systems Technology, Coating Technology for X-Ray-UV-OIR, and Free-Form Optics
PROPOSAL TITLE:
 Blazed Holographic Gratings with Aberration Correction on Freeform Mirror Surfaces for DUV Instruments
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Spectrum Scientific, Inc.
16692 Hale Avenue, Suite A
Irvine, CA 92606
(949) 260-9900

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
David Cook
E-mail:
david.cook@ssioptics.com
Address:
16692 Hale Ave Suite A Irvine, CA 92606 - 5052
Phone:
(949) 260-9900

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Grant DeCastro
E-mail:
grant.decastro@ssioptics.com
Address:
16692 Hale Ave Suite A Irvine, CA 92606 - 5052
Phone:
(949) 260-9900
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

The combination of multiple surface functionality into a single optical surface has been used for years as a method of improving system performance while reducing component count and system integration complexity. Further developments of this technology via combination of a diffraction grating and a freeform surface are explored. Multiple methods of combination are investigated. These include holographically recording a diffraction grating on a freeform substrate and by recording both the diffraction grating and freeform surface as holograms on a single substrate.

Tighter pack­aging constraints and performance requirements on exploratory missions such as LUVOIR are driving the need for more efficient and compact designs. Applying aberration corrected holographic gratings to a freeform surface has paradigm-shifting potential for these instruments with the potential for higher performance and throughput using fewer components.

Both efficiency and stray light are critical issues for upcoming missions. SSI proposes the use of a low scatter optical blazing technique in combination with a freeform optical surface as a means of supporting demanding spectral sensing requirements.

These innovations will significantly improve performance of next generation spectral sensing technologies by reducing system size and weight while improving imaging performance, signal-to-noise, energy collection, stray light and field of view.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA projects are dependent on optical systems and are constantly striving for improved throughput and reduced payload scale. The technology proposed is a direct solution for optimization to both of these considerations. Current and future applications include:

-LUVOIR and other Decadal Survey Missions

-CubeSat optical payloads

-Exo-Planet exploratory missions

-Space Life and Physical Sciences Research & Applications

-Future NASA & NOAA collaboration projects

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The potential for non-NASA commercialization is nearly applicable to all systems using diffractive optical elements. The reduced component count and improved throughput offered can be taken advantage of in Telecommunication, Augmented Reality, and Life Science. The added cost reduction benefit of replication fabrication techniques will open this technology to high volume commercial applications.

Duration: 6

PROPOSAL NUMBER:
 20-1- H9.07-6124
SUBTOPIC TITLE:
 Cognitive Communication
PROPOSAL TITLE:
 SpaceWeaver: A Collaborative Smart Network for Space Communications
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Rebel Space Technologies, Inc.
1747 East 2nd Street
Long Beach, CA 90802
(310) 819-2348

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Carrie Hernandez
E-mail:
carrie@rebelspacetech.com
Address:
1747 E 2nd St Long Beach, CA 90802 - 5917
Phone:
(310) 819-2348

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Carrie Hernandez
E-mail:
carrie@rebelspacetech.com
Address:
1747 E 2nd St Long Beach, CA 90802 - 5917
Phone:
(310) 819-2348
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

Rebel Space Technologies, Inc. proposes SpaceWeaver, a distributed cognitive space communications network to increase mission science data return, improve resource efficiencies for NASA missions and communication networks and ensure resilience in the unpredictable space environment. SpaceWeaver senses, detects, adapts, and learns from its experiences and environment to optimize the network's communications capabilities and reduce both the mission and network operations burden. SpaceWeaver leverages the latest advances in Artificial Intelligence and reinforcement learning to coordinate and control the transfer and relay of mission data across the lunar architecture based on data priority, content, schedule, and environmental conditions. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

SpaceWeaver uses Artificial Intelligence enhanced distributed sensing and optimized data routing to ensure efficient, resilient operations in the space environment. In addition to lunar communications architecture, the innovations proposed could also improve the mission data relay and network capabilities of the NOAA Satellite Information System, NASA Earth Science Mission Directorate systems, or the NASA Tracking and Data Relay System (TDRS).

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Applications include Department of Defense future space architectures and satellite communications networks, and commercial space industry (e.g., Earth remote sensing constellations, asteroid mining, deep space communications).

Duration: 6

PROPOSAL NUMBER:
 20-1- H9.01-6159
SUBTOPIC TITLE:
 Long Range Optical Telecommunications
PROPOSAL TITLE:
 Miniaturized Free Space Optical Communication Transceivers for CubeSats
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Freedom Photonics, LLC
41 Aero Camino
Santa Barbara, CA 93117
(805) 967-4900

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Donald Kebort
E-mail:
dkebort@freedomphotonics.com
Address:
41 Aero Camino Goleta, CA 93117 - 9311
Phone:
(805) 967-4900

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Leif Johansson
E-mail:
leif@freedomphotonics.com
Address:
41 Aero Camino Santa Barbara, CA 93117 - 3104
Phone:
(805) 277-3031
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

Freedom Photonics proposes to develop revolutionary miniaturized Free Space Optical Communication (FSOC) transceivers that are so compact that they are suited for CubeSats. The transceiver will realize low cost, size, weight and power through high power Photonic Integrated Circuit (PIC) technology and non-mechanical beam steering technology. Unlike RF, FSOC is inherently power efficient due to the high antenna gain from small optical wavelengths and is hard to detect and intercept. Operating in optical bands with orders of magnitude greater bandwidth, FSOC transceiver would be of great benefit to ease the bandwidth crowding in RF small satellite communications. Compact FSOC transceiver would be of great utility for civilian satellites requiring communication bandwidth without the competition for licensing crowded RF spectrum. Modular orbital FSO relays acting as cross-links and deep-space transceivers would mitigate the atmospheric effects and provide spatial redundancy for ground links.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA related applications targeted by this program are:
•    Scientific LEO CubeSat-ground communication relieving the RF crowding from ever growing number of CubeSats
•    GEO-LEO cross-links and LEO-Ground uplink relays to mitigate asymmetric atmospheric effects
•    Deep Space-GEO, GEO-LEO, LEO-Ground FSO relays providing spatial redundancy 
 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

•    Inter-satellite and satellite to ground communications (Satcom)
•    Low Probability of Intercept/Detection (LPI/LPD) communications for Special Operation Forces (SOFs)
•    Temporary deployment of secure high capacity computer networks
•    Broadband access for low density rural communities
•    Mobile communications for disaster and emergency management, Law enforcement and Fire Department

Duration: 6

PROPOSAL NUMBER:
 20-1- H3.03-5980
SUBTOPIC TITLE:
 Lunar Dust Management Technology for Spacecraft Atmospheres and Spacesuits
PROPOSAL TITLE:
 Cyclone Precipitator Sub-Micron Particulate Separator
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Mainstream Engineering Corporation
200 Yellow Place
Rockledge, FL 32955
(321) 631-3550

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Michael Blaise
E-mail:
mblaise@mainstream-engr.com
Address:
200 Yellow Place Rockledge, FL 32955 - 5327
Phone:
(321) 631-3550

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Michael Rizzo
E-mail:
mar@mainstream-engr.com
Address:
200 Yellow Place Rockledge, FL 32955 - 5327
Phone:
(321) 631-3550
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

During previous planetary exploration missions, deleterious effects have been observed due to fine particulates including fouling mechanisms, altering thermal properties, obscuring optical systems, abrading textiles, and scratching surfaces. With near term goals to return to the Moon, lunar dust is of particular concern and can potentially negatively affect every lunar architecture system. To mitigate this concern, Mainstream proposes to leverage our knowledge garnered for cyclone precipitators currently being developed as a particulate concentrator for the Radionuclide Aerosol Sampler/Analyzer (RASA). This concentrator uses 32 single-stage cyclone separators in parallel allowing for 16.7 CFM with a pressure drop across the system of 1.5 kPa. Separation efficiencies are >99% for >1 mm; 96% for 0.5 mm; and 80% for 0.2 mm. For Phase I, we will utilize our existing robust CFD and in-house cyclone optimization toolset to modify the RASA concentrator geometry to better reflect NASA’s separator requirements (i.e. lower volumetric flow rate, lower pressure drop). We will then design the precipitator to enhance the cyclone’s sub-micron efficiency and validate performance predictions using bench-scale experiments. Finally, we will design the full-scale system to determine size, weight, and power requirements. In Phase II, we will design, fabricate, and validate a full-scale prototype.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA applications for the proposed cyclone precipitator sub-micron particulate separation system include future manned missions such as Gateway and Mars including both general air purification of the main cabin of the manned spacecraft as well as the removal of planetary dust from main cabins and airlocks of the planetary habitat.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Non-NASA applications are numerous including nuclear radiation sensors (RASA and ARSA), industrial separators, commercial/medical/residential air purification, and particulate concentrators for detection apparatus. With respect to additional manned spacecraft, non-government commercial entities such as Space-X, Blue Origin, Bigelow Aerospace, and others include space tourism as a future goal.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z13.02-6369
SUBTOPIC TITLE:
 Dust Tolerant Mechanisms
PROPOSAL TITLE:
 Self-Cleaning Dust Proof Fluid and Gas Connector
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Off Planet Research, LLC
5700 Lacey Boulevard Southeast
Lacey, WA 98503
(253) 391-0293

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Vincent Roux
E-mail:
vince@offplanetresearch.com
Address:
5700 Lacey Blvd SE Lacey, WA 98503 - 7218
Phone:
(253) 391-0293

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Vincent Roux
E-mail:
vince@offplanetresearch.com
Address:
5700 Lacey Blvd SE Lacey, WA 98503 - 7218
Phone:
(253) 391-0293
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

We will develop a self-cleaning dust and regolith tolerant fitting that will enable either gas or fluid transfer on the Moon, Mars, or other worlds.  The fitting will not rely on soft seals that will quickly become brittle in space.  The fitting design is well suited for use in the ultra-cold permanently shadowed regions of the Moon and will be adaptable for quick operation automatically or by a suited astronaut.

 

The fitting will achieve reliable, long-term, repeated use in the dusty environments off Earth with negligible loss of product by employing several layers of passive and active dust mitigation including an internal gas-purge system to remove dust from the fitting threads and sealing faces, threads that can function without jamming in the presence of regolith dust, surface geometries that reduce the concentration of electro-static charges, and ultra-smooth surfaces to eliminate locations that dust particles can be trapped.  The fitting will be electro-statically grounded to its system.

 

The fitting will have a dust cover and a gas-operated cleaning cuff for removing dust before the fitting is operated. The gas flow to clean the threads and sealing surfaces can be supplied to the fitting either through the attaching system itself or by a separate gas supply bottle as needed.

 

In Phase 2 the fitting will be further developed to include electrostatic dissipative (ESD) coatings and a vibrational source, such as a small external ultrasonic transducer or from a clicking feature in the nut similar to a socket wrench, which will produce vibrations while the nut is being turned to help knock loose dust and regolith particles throughout the fitting.  An in-line filter will be downstream of the fitting to trap any dust that may make its way past the fitting.

 

The knowledge gained and many of the innovations in this fitting can be applied to other types of lunar technology, providing multiple returns for the funding.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

These fittings are well suited for any landed mission on the Moon or other worlds. These fittings can help assure the success of re-fueling from ascent vehicles that may carry dust to orbiting spacecraft.

 

The fittings are adaptable to automated or human operation, can operate in the permanently shadowed regions of the Moon, and will be able to transfer cryogenic rocket fuels and oxidizers. The fitting can be sized to meet various needs, and its innovations can be applied to other technologies.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Any lost product is expensive regardless of where it is lost, but commercial operations on other worlds must be able to successfully transfer valuable commodities like oxygen and rocket fuel with minimal loss or they will fail.These connectors can help prevent spills in dusty locations in the chemical, oil, and gas industries on Earth, reducing environmental damage and legal risks of leaks.

Duration: 6

PROPOSAL NUMBER:
 20-1- A3.03-6425
SUBTOPIC TITLE:
 Future Aviation Systems Safety
PROPOSAL TITLE:
 Virtual Environment for Informative Analysis Framework’s Process: A Mixed-Reality System for Safely Enabling Human-Automation Interaction and Teaming
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
TRACLabs, Inc.
100 North East Loop 410, Suite 520
San Antonio, TX 78216
(281) 461-7886

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Ernest Cross II
E-mail:
vince.cross@traclabs.com
Address:
100 North East Loop 410, Suite 520 San Antonio, TX 78216 - 4727
Phone:
(856) 887-1791

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
David Kortenkamp
E-mail:
korten@traclabs.com
Address:
100 North East Loop 410, Suite 520 San Antonio, TX 78216 - 1234
Phone:
(281) 461-7886
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Addressing the challenges associated with dramatic increase in the complexity of the National Airspace System (NAS) has required the introduction of autonomous capabilities to maintain efficiency and safety. However, as increasingly autonomous (IA) capabilities and systems are introduced into existing human-centric environments, the roles and responsibilities of humans change, especially when working in collaborative environments, such as the Airport Operations Area (AOA) and Urban Air Mobility (UAM). The integration of autonomous capabilities into traditionally human-centric environments with the goal of Human-Automation Interaction and Teaming (HAIT) makes it difficult for IA systems to not be brittle (i.e., working well in the lab under nominal circumstance, but perform poorly in unexpected situations) and accident-prone (i.e. account for emergent behavior due to unexpected decision by people or environment changes) as they attempt to work collaboratively with people. Therefore, we propose the Virtual EnviRonment for InFormative analYsis (VERIFY) framework, which links physical spaces to a virtual environment (i.e. mixed-reality). VERIFY will be used as a research tool for proactively understanding how humans and IA systems will need to work collaboratively to address and mitigate system hazards and unexpected events as a HAIT. By using a mixed-reality environment, researchers can explore multiple environmental variables simultaneously, to understand their impact on individual tasks across multiple HAIT arrangements. The objective is to leverage use cases to define key characteristics for probabilistic scenario generation to define HAIT test cases for evaluation within a mixed-reality environment. This approach also enables engineers to safely employ both physical and virtual hazards for training adaptive and non-deterministic systems and human operators to work alongside each other under nominal and off-nominal conditions.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

A variety of NASA technologies and missions could benefit from this effort, e.g, ISS robots: Astrobee and R2, OSAM system Restore-L, the in-Space Assembled Telescope, the Lunar Surface Science Mobility System, Commercial Lunar Payload Services, and future manned Mars missions. There are also research topics within NASA’s Human Research Program that are funding human-automation interaction and teaming topics. Finally, there are various STMD technology demonstrations that would also benefit.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The designs and techniques developed under this project will have direct application to human-automation interaction and teaming efforts with TRACLabs DOD customers, e.g. the Air Force Space and Missile Systems Center, U.S. Army TARDEC, and the Army Futures Command. Additional customers integrating IA systems into human-centric environments include automotive, and oil & gas manufactures.

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.05-6576
SUBTOPIC TITLE:
 Detector Technologies for UV, X-Ray, Gamma-Ray Instruments
PROPOSAL TITLE:
 Solar Blind UV APD based on III-N Material System for UV Spectroscopy and Imaging Applications
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Banpil Photonics, Inc.
4800 Patrick Henry Drive, Suite 120
Santa Clara, CA 95054
(408) 282-3628

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Achyut Dutta
E-mail:
akdutta@banpil.com
Address:
4800 Patrick Henry Dr. Suite 120 Santa Clara, CA 95054 - 1820
Phone:
(408) 282-3628

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Achyut Dutta
E-mail:
akdutta@banpil.com
Address:
4800 Patrick Henry Dr. Suite 120 Santa Clara, CA 95054 - 1820
Phone:
(408) 282-3628
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 2
Technical Abstract (Limit 2000 characters, approximately 200 words)

This Small Business Innovation Research (SBIR) project seeks to develop  avalanche photodiode (APD) and its array, for solar-blind detection in UV wavelengths ranging from 200 nm to 250 nm for  space applications. The solar-blind UV APD is based on III-nitride (III-N) technology.  The ultra-wide bandgap (UWB) of AlXGa1-XN material system enables to achieve highly efficient, radiation-hard detectors capable of operating at high temperatures in the solar-blind UV regime without the need for external filters. The proposed solar-blind UV-APD will be capable to have high gain and low dark current (few pico amperes) so that the array of which can be used for solar blind imaging.  In Phase I, we will perform material growth and characterization to achieve high quality AlGaN material system, verifying the material quality and performance in the solar blind ranges by making device. Design-simulation of APD device follows to optimize the structural parameters. In Phase II, the proposed solar-blind UV APD devices will be further optimized, fabricated, packaged as arrays and evaluated for high multiplication gain and low noise performance. We anticipate achieving a sufficiently high yield on large area substrates for economic production of large format for space applications as well as defense, and commercial bio-chemical systems applications.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

UV spectroscopy and imaging instruments require UV detection capabilities. UV emission lines and bands from H, C, O, N, S, OH and CO; UV absorption lines by CO2, H2O, NH3, N2; and UV surface reflectance spectra are essential for detection ice, iron oxides, organics, and other compounds on planetary bodies. Future NASA missions include: New Horizons (NH) mission to Pluto, and Lyman Alpha Mapping Project (LAMP) instrument on Lunar Reconnaissance Orbiter (LRO) mission. NASA mission of relevance is the Large UV Optical Infrared Surveyor (LUVOIR). 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Commercial and defense applications includes detection of bio-chemical species and explosives in  a form of detection system that is compact, portable identification systems for warfighters and first responders. Defense also includes early missile threat warning and free-space communications. Commercial applications include industrial, lab instrument, and consumer UV monitoring.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z7.03-5096
SUBTOPIC TITLE:
 Deployable Aerodynamic Decelerator Technology
PROPOSAL TITLE:
 High Temperature Flexible Aerogel Insulation for Extreme HIAD Environments
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
S. D. Miller and Associates, PLLC
216 West Cherry Avenue, Building 2
Flagstaff, AZ 86001
(928) 779-5000

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Steve Miller
E-mail:
smiller@sdmatech.com
Address:
216 West Cherry Avenue, Building 2 Flagstaff, AZ 86001 - 4424
Phone:
(928) 779-5000

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Steve Miller
E-mail:
smiller@sdmatech.com
Address:
216 West Cherry Avenue, Building 2 Flagstaff, AZ 86001 - 4424
Phone:
(928) 779-5000
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

While working on NASA’s Convective Heating Improvement for Emergency Fire Shelters (CHIEFS) effort, S. D. Miller & Associates (SDMA) developed methods of embedding materials into fiber matrices to enhance their thermal properties.  Silica aerogel was embedded into an alumina fiber matrix to create Flexible Insulation with a Reinforced Aerogel (FIRA).  In the current Phase I effort, a High Temperature FIRA (HTFIRA) will be demonstrated by embedding aerogel with a higher temperature capability.  Since commercially available aerogel blankets are currently limited to 1200OF, producing HTFIRA with a scalable manufacturing process would be a significant advance in the state-of-the-art.  The re-entry trajectory and payload capacity of Hypersonic Inflatable Aerodynamic Decelerators (HIADs) are limited by the materials in the Thermal Protection System (TPS).  For example, the TPS on the LOFTID (Low-Earth Orbit Flight Test of an Inflatable Decelerator) uses carbon felt and silica aerogel that degrade during re-entry when temperatures can exceed 2800OF.  Replacing all or part of these layers with HTFIRA will allow higher heating rates without degradation, facilitating heavier payloads and more direct re-entry trajectories.  HTFIRA will also be more flexible, lighter and more compact than the existing TPS materials, further increasing the payload capacity of HIAD.  In Phase I, SDMA will collaborate with NASA Glenn Research Center to make aerogel.  SDMA will then embed that aerogel in an alumina fiber matrix to demonstrate HTFIRA.   Thermal properties will be determined.  In a parallel effort in preparation for Phase II and III, SDMA will investigate the scalability of the aerogel manufacturing process and the compatibility of HTFIRA with the fabrication methods developed for the TPS of LOFTID.  HTFIRA promises a significant improvement in TPS for multiple Entry, Descent and Landing (EDL) strategies including HIAD and controlled flight through planetary atmospheres.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA will test LOFTID in 2022.  Future inflatable decelerators will be used for getting humans to the surface of Mars, to recover booster engines after launch, to haul equipment back from the International Space Station, to return materials like fiber optic cables manufactured in space, and as emergency evacuation vehicles for crews working in orbit.  HTFIRA will reduce the weight and bulk of the TPS on these vehicles, increasing the capacity for fuel and payload, and allow better optimization of the re-entry trajectory.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

HTFIRA will let commercial space companies deliver payloads to Mars for less money. Whether you use rockets or inflatable decelerators to land on Mars, the thin atmosphere and larger payloads mean higher heating rates. HTFIRA will reduce costs by enabling larger payloads.  Other applications will include more efficient car engines, safer electric batteries and reduced damage from fires.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z5.04-5434
SUBTOPIC TITLE:
 Technologies for Intra-Vehicular Activity Robotics
PROPOSAL TITLE:
 Advanced planning capabilities for humanoids in microgravity environments
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
PickNik Inc
1942 Broadway, Suite 222
Boulder, CO 80302
(720) 513-2221

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Mark Moll
E-mail:
mark@picknik.ai
Address:
1942 Broadway Ste 222 Boulder, CO 80302 - 5213
Phone:
(713) 775-7621

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Dave Coleman
E-mail:
dave@picknik.ai
Address:
1942 Broadway Ste 222 Boulder, CO 80302 - 5213
Phone:
(720) 513-2221
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

To increase robot autonomy it is necessary that a robot can reason over longer time lines than is currently possible with minimal input of a human operator. We propose to develop a system (on top of ROS 2 and MoveIt 2) that enables operators to command humanoids at a high level while still have the robot's motions satisfy task-specific low-level motion constraints. This is done in two steps. First, we will develop several parametrized primitives that allow an operator to specify a broad range of constrained motions, including climbing in microgravity, turning valves, and opening doors. Second, we will develop a task construction framework that allows an operator to compose such primitives into much larger tasks. The task construction framework will be able to compute complete end-to-end continuous motion plans that satisfy all relevant motion constraints. The operator will be able to preview these plans and select one for execution. We will also develop appropriate user interfaces that allow operators to specify complex tasks without having to write any code.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed system would enable operators to specify complex sequences of motions for humanoid robots (such as Robonaut 2) in microgravity environments like the International Space Station or the Gateway. The system will automatically compute feasible paths that can be selected by the operator for execution. Applications of the system include (but are not limited to) planning humanoid climbing motions aboard the ISS or Gateway, opening valves/doors, and retrieving bags from storage.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

In warehouse logistics, manipulators often need to complete a series of pick-and-place operations. Such a task can be completely specified using our system by an operator who does not need to be a robotics expert. Besides order fulfillment in warehouses, applications include remote operation of inspection or search and rescue robots. Eventually, assembly or food preparation tasks could be enabled.

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.10-5445
SUBTOPIC TITLE:
 Atomic Interferometry
PROPOSAL TITLE:
 Comb Using Photonically Integrated Devices (CUPID)
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Vector Atomic, Inc.
1249 Quarry Lane Suite 100
Pleasanton, CA 94566
(925) 249-5959

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Arman Cingoz
E-mail:
arman@vectoratomic.com
Address:
1249 Quarry Lane, Suite 100 Pleasanton, CA 94566 - 8410
Phone:
(925) 249-5959

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Jason Burke
E-mail:
jason@vectoratomic.com
Address:
1249 Quarry Ln, Suite 100 Pleasanton, CA 94566 - 8410
Phone:
(925) 249-5959
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Optical frequency combs play an essential role in modern timekeeping and metrology. To date, however, frequency combs are primarily used in laboratories, owing to their size, weight, power, and cost (SWaP-C) and fragility. To operationalize the technology, Vector Atomic and Harvard University will design an erbium (Er) fiber Comb Using P hotonic Integrated Devices for supercontinuum generation and self-referencing. CUPID will combine the robust Er fiber comb architecture with an integrated  photonics module for supercontinuum generation and self-referencing. CUPID will provide < 10-17 excess fractional instability at 1 s, in a compact package at low power and manufacturing cost.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Space missions are critically dependent on precise timing and synchronization. Coherent ranging and imaging systems such as the Laser Interferometer Space Antenna (LISA) and the NASA-ISRO Synthetic Aperture Radar Mission (NISAR) are enabled by highly coherent RF and laser oscillators, respectively. Future NASA mission including deep space navigation, space-based gravitational wave detectors, and multi-static radar imaging will require timing precision beyond the capabilities of current hardware.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

LiDAR and RADAR applications can benefit from the long coherence time of the optical local oscillator and the ultralow phase noise provided by the frequency comb. In GPSdenied environments, a highly stable clock can extend missions by maintaining synchronization between distributed systems.

Duration: 6

PROPOSAL NUMBER:
 20-1- H3.03-6094
SUBTOPIC TITLE:
 Lunar Dust Management Technology for Spacecraft Atmospheres and Spacesuits
PROPOSAL TITLE:
 Lunar Dust Filter for Spacecraft Atmospheres
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Blazetech Corporation
29 B Montvale Avenue
Woburn, MA 01801
(781) 759-0700

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Vijay Devarakonda
E-mail:
venkat@blazetech.com
Address:
29 B Montvale Avenue Woburn, MA 01801 - 7021
Phone:
(781) 759-0700

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
N. Albert Moussa
E-mail:
amoussa@blazetech.com
Address:
29 B Montvale Avenue Woburn, MA 01801 - 7021
Phone:
(781) 759-0700
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Dust poses unique challenges in space missions. This proposal addresses the development of an advanced self-cleaning staged dust filter for spacecraft air purification in cabin and airlock chambers. This technology is compact and autonomous, has low power requirement and is effective for various types of dust including the particulate matter derived from materials, ECLSS and other processes, and biological matter and debris generated by the crew, and lunar dust intrusion. Phase I research focuses on the design, construction and testing to determine the feasibility of this system in filtering simulated dust from air at atmospheric pressure.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The primary intended application of the proposed filter is in the purification of air in the pressurized compartments of the spacecraft in lunar mission. The secondary NASA application is the extension of this technique to other systems like the dust filtration in the ISS and collection of carbon particles and hydrocarbon dust in the NASA Environmental Control and Life Support.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

BlazeTech’s filter technology can be extended to other applications where filtration without significant use of manpower is a priority. Examples include filtration of sand from gas streams that enter the engine compartments in helicopters and aircraft, and separation of fine particulate contaminants from emissions from chemical process industry and smoke-stacks in power plants.

Duration: 6

PROPOSAL NUMBER:
 20-1- H5.02-6147
SUBTOPIC TITLE:
 Hot Structure Technology for Aerospace Vehicles
PROPOSAL TITLE:
 Through Thickness Reinforcement of Tubular and Conical Preforms for Hot Structure Applications
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
T.E.A.M., Inc.
841 Park East Drive
Woonsocket, RI 02895
(401) 762-1500

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Aaron Tomich
E-mail:
atomich@teamtextiles.com
Address:
841 Park East Drive Woonsocket, RI 02895 - 6112
Phone:
(401) 762-1500

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Aaron Tomich
E-mail:
atomich@teamtextiles.com
Address:
841 Park East Drive Woonsocket, RI 02895 - 6112
Phone:
(401) 762-1500
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

C-C material systems have high strength:weight ratios at high temperatures, making them well suited for future hot structure designs.  However legacy C-C solutions are subject to poor through thickness properties (for 2D laminates), or manufacturing speed and capacity issues (for Cartesian billets.)  These issues are often compounded for tubular or conical geometries.  

 

With this SBIR Phase I submission TEAM, Inc. proposes to advance the state art for tubular and conical preforming methods for use in C-C hot structure applications.  A parallel process development and testing program is proposed: 

 

Process Development:  We will use “off the shelf” and versatile braiding technology to demonstrate fabrication of conical, carbon fiber preform(s) with up to 1” wall thickness and conical geometry.  We will modify TEAM's custom designed, automated z-stitching line to insert stitches into a conical geometry preform at controlled and repeatable spacing(s). 

 

Testing Program:

In parallel with the process development, we will quickly fabricate flat panel test coupons of stitched and un-stitched braided laminates. (A phenolic-resin system will be used to meet cost and schedule constraints in Phase I.)  ~Half the panels will be tested by partner Southern Research Institute to characterize in-plane and inter-laminar tensile properties of stitched vs. un-stitched variants.  The other ~half of panels will be delivered as-is for potential C-C densification and testing by NASA or by TEAM at beginning of Phase II. 

 

The advantage of the proposed approach is that both the braiding process and the stitching work cell are easily scaled in terms of part size and geometry.  Through thickness property issues with traditional C-C tape-lay are addressed by the proposed stitching process.  Cost / capacity / geometric constraint issues associated with Cartesian / Polar billets are addressed by versatility and relative speed of the braiding and z-stitching processes.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Potential NASA users of this technology exist for a variety of propulsion systems, including upper stage engine systems, in-space propulsion systems, Lunar/Mars lander descent/ascent, solid motor systems, including those for primary propulsion, hot gas valve applications, and small separation and/or attitude control systems.  Potential programs of interest include Commercial Orbiter Transportation Services (COTS), Commercial Lunar Payload Services (CLPS) and NASA HEOMD programs including Space Launch System (SLS) and Human Landing System (HLS).  

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed C-C preforming & material system proposed here-in is of great interest to various DoD stakeholders currently developing hypersonic missile and vehicle systems.  (Army, Navy, Air Force, DARPA and their prime contractors).   The technology would likely be applied as TPS or hot structure for aeroshell bodies, frustras, nose-tip adaptors, leading edges and other control surfaces. 

Duration: 6

PROPOSAL NUMBER:
 20-1- Z8.09-6257
SUBTOPIC TITLE:
 Small Launcher Lunar Transfer Stage Development
PROPOSAL TITLE:
 Moon Express - Green Propellant Lunar Transfer Stage
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Lynntech, Inc.
2501 Earl Rudder Freeway South
College Station, TX 77845
(979) 764-2200

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Michael Martin
E-mail:
michael.martin@lynntech.com
Address:
2501 Earl Rudder Freeway South College Station, TX 77845 - 6023
Phone:
(979) 764-2200

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Darla Hisaw
E-mail:
darla.hisaw@lynntech.com
Address:
2501 Earl Rudder Freeway South College Station, TX 77845 - 6023
Phone:
(979) 764-2219
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

NASA is returning to the Moon in 2024 with the Artemis mission and will need an array of satellites in lunar orbit to provide communications, navigation information, and scientific data to personnel on the Moon and Earth. There is a need to develop a lunar transfer stage for small rocket launch vehicles to deliver a 25 kg satellite payload to lunar orbit. This transfer stage needs to be capable but compact. It should also be low cost and safe, which can be achieved by utilizing new non-toxic “green” propellants. Lynntech, along with a large industry team and AFRL, proposes to use a proprietary “green” monopropellant engine and PMD tank to develop a transfer stage that is compact, efficient, and cost-effective for the delivery of payloads. This monopropellant was flight-proven in 2019 and is ready for general use. In Phase I, we will define the mission, perform analysis, ground-test a propulsion element, and identify all necessary components and team members in preparation for demonstration and delivery in Phase II.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed technology can be utilized to transfer satellites from TLI to NRHO as well as to orbit other planets in support of NASA missions. Lynntech’s revolutionary engine could enable low-cost exploration of the Solar System while making launch operations safer. The engine is scalable so higher thrust levels are achieved with minor changes to the injector, enabling necessary delta-V burns. Our proprietary PMD technology could also allow for effective square or rectangular PMD tanks that maximize space utilization aboard CubeSats.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed technology is of general applicability to rocket transfer stages from LEO to GEO (for military and commercial satellites). The growth of the orbital economy will depend on low-cost movement and placement of satellites which this system will provide. The propulsion system could also be used to create agile satellites for greater survivability in military operations.

Duration: 6

PROPOSAL NUMBER:
 20-1- A3.03-6314
SUBTOPIC TITLE:
 Future Aviation Systems Safety
PROPOSAL TITLE:
 Strategic Cybersecurity Framework for UTM-ISSA
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Vcrsoft, LLC
3513 Napolean Court
Plano, TX 75023
(817) 213-6184

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
VC Ramesh
E-mail:
vcr@vcrsoft.com
Address:
3513 Napolean CT Plano, TX 75023 - 7050
Phone:
(817) 213-6184

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
VC Ramesh
E-mail:
vcr@vcrsoft.com
Address:
3513 Napolean CT Plano, TX 75023 - 7050
Phone:
(817) 213-6184
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

NASA's UTM-ISSA architecture has 3 layers where the Monitor-Assess-Mitigate (MAM) components of ISSA are situated: at the UAS level (vehicle system functions), at the Ground Control Station (GCS) level (GCS functions), and at the Supplemental Data Service Provider (SDSP) level (SDS services). We modify this by adding an extra intermediate layer at the UAS Service Supplier (USS) level (USS functions). The aim of the proposed effort is to develop and demonstrate a strategic cybersecurity framework for this UTM-ISSA architecture. While there are many risk factors that impact ISSA, we focus on risks that emanate from cybersecurity threats from a variety of players. 

For the monitor portion, we propose an approach to aggregate a variety of cybersecurity-relevant data sources at various levels of the UTM-ISSA. Designing the information schema for these data elements is part of the proposed effort. We divide the Assess portion into two: Assess-1 and Assess-2. The Assess-1 portion involves a signature-based misuse detection for cybersecurity threats followed (sequentially) by a deep learning based anomaly detection module. The Assess-2 takes as input the anomalous patterns from Assess-1 and provides strategic labels: Who?, What?, Why?, How? and When? based on a deep learning multi-label classifier. The Mitigate component uses an attack tree for devising strategic countermeasures and a game theory module for devising tactical countermeasures corresponding to each strategy at each level of the UTM-ISSA.

We propose to demonstrate the feasibility of the proposed approach using an illustrative cyber-terrorist scenario that features a coordinated cybersecurity attack on multiple UAS.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA's UTM-ISSA program is the first anticipated tech transfer target and application. NASA's UAM program is the next anticipated application. NASA has many other programs, such as the Mars Rover and Counter-UAS, that will benefit from the strategic cybersecurity framework developed in this research.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The Department of Homeland Security (DHS) and the Department of Defense (DoD) have many cybersecurity, counter-UAS and counter-swarm programs that will benefit from the proposed framework. In the private security, many drone/UAS as well as USS vendors are likely targets for commercialization.

Duration: 6

PROPOSAL NUMBER:
 20-1- H9.03-5245
SUBTOPIC TITLE:
 Flight Dynamics and Navigation Technology
PROPOSAL TITLE:
 Suite of Lagrangian Coherent Structure (SuiteLCS) Software
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
CU Aerospace, LLC
3001 Newmark Drive
Champaign, IL 61822
(217) 239-1703

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ryne Beeson
E-mail:
beeson@cuaerospace.com
Address:
3001 Newmark Drive Champaign, IL 61822 - 1474
Phone:
(847) 847-9709

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
David Carroll
E-mail:
carroll@cuaerospace.com
Address:
3001 Newmark Dr Champaign, IL 61822 - 1474
Phone:
(217) 239-1703
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

CU Aerospace (CUA) proposes development of a professional suite of software using the mathematical theory of Lagrangian coherent structures (LCS) to enable engineers and scientists from a wide range of disciplines to study, investigate, engineer and optimize systems dependent on chaotic, turbulent or unsteady flows. The Suite of Lagrangian Coherent Structure (SuiteLCS) software that CUA proposes to develop will be the first commercially and professionally available software package of its kind - enabling NASA engineers to propose and plan missions with new capabilities by identifying trajectories in Earth-Moon, cislunar, deep-space, or multi-body environments that have particular qualitative behavior, allowing engineers to find long term stable trajectories or those with minimum fuel usage and fast transit times. SuiteLCS will provide a complete generalization to dynamical structures used by NASA engineers in simplified dynamical models (CR3BP) - providing a high fidelity tool replacement for preliminary mission planning, broadening the mission search space and accelerating the mission design phase. SuiteLCS will be built on robust and high-quality development standards, using exceptional internal and open source external packages to accelerate development and successfully complete the Phase I technical objectives. The software will leverage parallel computing on distributed (MPI) and shared (OpenMP) memory architectures to reduce run-times. Phase II efforts may look to port parallel computation to cloud computing resources. The professional and open source Paraview and VTK software will be used for standardized import/export capability and high-quality visualization of potentially extremely large data sets. CUA anticipates that a Phase II delivery of SuiteLCS will have an immediate impact on mission design capabilities at NASA: enabling new mission concepts, earlier mission studies at higher fidelity, and broadening the mission search space. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

SuiteLCS addresses the lack of existing software for identifying and analyzing coherent structures based on a Lagrangian approach in chaotic, turbulent or mixing fluids. For astrodynamics, SuiteLCS will meet NASA's Technology Roadmap goals of advanced modeling and simulation tools that allow for expanded solution spaces enabling new design concepts and at higher fidelity.  A Phase II SuiteLCS will further enable branches of NASA in their study and design of systems ranging from Earth/space weather, aeronautics, and capsule entry design. 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

SuiteLCS will enable academia, research centers, and industry to continue wider and deeper application of LCS to critical scientific questions, including: climate, atmospheric and ocean science, biology, unsteady airflow over airfoils, parameter estimation, and spacecraft trajectories and mission design. SuiteLCS will provide the only commercial and professional software for these experts. 

Duration: 6

PROPOSAL NUMBER:
 20-1- Z3.03-5627
SUBTOPIC TITLE:
 Development of material joining technologies and large-scale additive manufacturing processes for on-orbit manufacturing and construction
PROPOSAL TITLE:
 Additive Friction Stir Deposition for In-Space Manufacturing
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
IERUS Technologies, Inc.
2904 Westcorp Boulevard, Suite 210
Huntsville, AL 35805
(256) 319-2026

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Greg Finney
E-mail:
greg.finney@ierustech.com
Address:
2904 Westcorp Blvd Suite 210 Huntsville, AL 35805 - 6437
Phone:
(256) 319-2026

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Billy Todd
E-mail:
billy.todd@ierustech.com
Address:
2904 Westcorp Blvd Suite 210 Huntsville, AL 35805 - 6437
Phone:
(256) 319-2026
Estimated Technology Readiness Level (TRL) :
Begin: 4
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

IERUS Technologies proposes to investigate utilization of additive friction stir deposition (AFS-D), to robotically fabricate and repair large structures in the external space environment. The AFS-D process, commercially known as MELD, provides a new path for coating, joining, repairing and additively manufacturing metals and metal matrix composites The MELD process produces fully-dense, near net-shape structures in open atmospheric conditions without secondary post processing. MELD is a fast, low-power, fully scalable, deposits almost any metal on the market and builds complex 3-D structures without support material. MELD also offers a unique opportunity for in-orbit recycling applications. The MELD process is a capable platform for recycling, using scrap metal chips and damaged components as feedstock to additively manufacture new. MELD could be the technique that unlocks in-space manufacturing potential while simultaneously mitigating orbital debris. The MELD additive manufacturing technique is well suited for on-orbit manufacturing and will bring tremendous advantages.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The advantages of the proposed In-space manufacturing stem include the ability to manufacture larger structures, lower launch costs, increased performance, longer satellite life, increased resilience, simplified logistics, and more sustainable spaceflight operations. NASA needs to be ready to move forward and continue scientific and technological advancements by proceeding with in-space manufacturing efforts now.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Commercial markets such as SpaceX’s Starlink satellite constellation are emerging that could greatly benefit from the proposed in space manufacturing concept. There also is a continued and constant interest for a commercial space station, that would undoubtedly need in-space manufacturing technologies in order to be successful and reach its true potential.

Duration: 6

PROPOSAL NUMBER:
 20-1- H3.01-5695
SUBTOPIC TITLE:
 Advancements in Carbon Dioxide Reduction: Critical Subsystems and Solid Carbon Repurposing
PROPOSAL TITLE:
 High Efficiency Hydrogen Separation Membrane Module for Space Oxygen Recovery Systems
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Bettergy Corporation
8 John Walsh Boulevard, Suite 321
Peekskill, NY 10566
(914) 426-2577

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Zhong Tang
E-mail:
ztang2003@yahoo.com
Address:
8 John Walsh Boulevard, Suite 321 Peekskill, NY 10566 - 5330
Phone:
(914) 368-7867

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Lin-Feng Li
E-mail:
crotonbusiness99@gmail.com
Address:
8 John Walsh Boulevard, Suite 321 Peekskill, NY 10566 - 5330
Phone:
(914) 290-6293
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

NASA is developing several technologies that have the potential to increase the percentage of oxygen recovery from carbon dioxide, toward fully closing the Air Revitalization System loop. Methane pyrolysis recovers hydrogen from methane, making additional hydrogen available to react with carbon dioxide. Bettergy proposes to develop a robust, highly efficiency hydrogen separation assembly enabling the separation of hydrogen from hydrogen, hydrocarbon rich streams for the oxygen recovery system in the ISS.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)
The technology developed in this project will provide robust Oxygen Recovery System to recover hydrogen from methane that can be directly used in ISS
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)
Successful completion of the current program will make significant contribution toward development of the new technologies that can effectively produce hydrogen from various sources for hydrogen refueling stations, fuel-cell vehicle fleets, and other applications.
Duration: 6

PROPOSAL NUMBER:
 20-1- H9.01-6342
SUBTOPIC TITLE:
 Long Range Optical Telecommunications
PROPOSAL TITLE:
 High Power and High Reliability Fiber Optical Routing Switch
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Photonwares Corporation
15 Presidential Way
Woburn, MA 01801
(781) 935-1200

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Guanghai Jin
E-mail:
gjin@photonwares.com
Address:
15 Presidential Way Woburn, MA 01801 - 1040
Phone:
(781) 935-1200

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Jim Zhao
E-mail:
JZHAO@PHOTONWARES.COM
Address:
15 Presidential Way Woburn, MA 01801 - 1040
Phone:
(781) 465-2600
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

Photonwares Corporation proposes a new design to realize a 1x2 high power fiber optical switch.  Our design incorporates several innovative features to achieve performance that is beyond state-of-the-art, meeting the requirements for NASA deep space long-range communication.   The proposed fiber optical switch design also leverages our over 20 years of micro-optic development experience to achieve extended longevity over 20 years without power consumption as well as meeting compact size and low weight requirements for space applications.  The design and fabrication process are compatible with and qualified for space applications.  The phase I effort will result in a prototype demonstration that supports performance claims and a Phase II plan that formulates a pathway to a space qualification with planned flight experiments in Phase III. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

This program addresses NASA's need to develop technologies for conducting future deep-space missions with extended communication range and flight time.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

RF-photonics, free-space communications, and quantum communication systems including unhackable communications, instantaneous teleporting communications, connecting quantum computers together.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z13.01-6344
SUBTOPIC TITLE:
 Active and Passive Dust Mitigation Surfaces
PROPOSAL TITLE:
 Integrated Approach for Space Active and Passive Dust Mitigation Enabled by Electroactive Polymer Technology
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
PolyK Technologies, LLC
2124 Old Gatesburg Road
State College, PA 16803
(814) 308-0778

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Shihai Zhang
E-mail:
energy@polyktech.com
Address:
2124 Old Gatesburg Road State College, PA 16803 - 2200
Phone:
(518) 605-6897

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Shihai Zhang
E-mail:
energy@polyktech.com
Address:
2124 Old Gatesburg Road State College, PA 16803 - 2200
Phone:
(518) 605-6897
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

The SBIR Phase I project will develop a dust mitigation technology for NASA’s planetary exploration missions. Specifically, this technology combines three dust removal mechanisms, including vibration, electrodynamic force, and superhydrophobic surface, and integrates them into a single laminate (PolyK Dust Mitigation Laminate, or PKDML). Once the PKDML is activated, dust particles will be bumped off the surface by vibration and steered away by electrodynamic force. The superhydrophobic surface reduces the adhesion between dust and surface, further facilitating dust movement and preventing dust accumulation. This technology can provide far more effective and efficient solution than the current state-of-the-art (electrodynamic dust shield, or EDS), as manifested at least in: 1) dust is transported in air rather than along the surface, which will save a significant amount of electrical energies that are otherwise needed to overcome the strong surface friction; 2) vibration is more effective in removing uncharged and large dust particles than the EDS technology. Moreover, the PKDML has similar structure layout to the EDS technology, enabling the fast manufacturing, installation, and adoption for the emerging NASA lunar and Mars missions.

The feasibility of this technology has been verified by out promising preliminary results. The in-depth experience and expertise in high voltage manipulation, electroactive polymers, actuator designs and applications, and manufacturing capability will greatly endorse this project.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The PKDML technology can be immediately applied in NASA exploration systems such as optical systems, including solar panels, camera lenses, and spacecraft viewports, as well as in active parts that need certain freedom of movement, such as spacesuit fabrics, rotary joints, and connectors. Furthermore, the electroactive polymer layer integrated in the PKDML is also a force sensor, and the weight and location of deposited dust can be monitored on a real-time basis to determine whether the dust cleaning is required (smart dust removal)

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

While the PKDML are designed for NASA applications, they can also be used in civilian and commercial applications, especially for solar panel cleaning, hard-to-reach surface cleaning.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z13.02-6350
SUBTOPIC TITLE:
 Dust Tolerant Mechanisms
PROPOSAL TITLE:
 High Power Near-Field Wireless Transfer for Dust Intensive Applications
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Astrobotic Technology, Inc.
912 Fort Duquesne Boulevard, 3rd Floor
Pittsburgh, PA 15222
(412) 682-3282

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Michael Provenzano
E-mail:
mike.provenzano@astrobotic.com
Address:
912 Fort Duquesne Blvd Pittsburgh, PA 15222 - 4613
Phone:
(845) 399-0843

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Michael Provenzano
E-mail:
mike.provenzano@astrobotic.com
Address:
912 Fort Duquesne Blvd Pittsburgh, PA 15222 - 4613
Phone:
(845) 399-0843
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

A great challenge with power management is the way power is transmitted to other devices. Traditional space systems operate through nuclear, solar, or tethered power mechanisms that require great complexity and process to qualify and operate. Tethered systems are hindered tremendously by mechanically mated components that are prone to regolith incursion and that require large robotically generated forces for interconnection. Furthermore, astronauts suffer from limited suit dexterity to manipulate and manage such systems. Nuclear powered systems require intensive handling procedures, and in many cases, presidential authority to launch—greatly increasing the cost and schedule of such missions. Solar powered systems require continuous access to the Sun and must follow predicated operational plans to maximize sunlight exposure and limit system duty cycles, ultimately constraining system performance. A wireless charging system would mitigate these challenges for standalone systems that don’t have the resources to generate power independently through the traditional methods listed above and would in many cases eliminate the need for some quick disconnect technologies used in static joints. Furthermore, a charging technology such as this could have great utility not only on the Moon, but also in critical space applications on Mars, in orbit, and beyond.

The proposing team of Astrobotic and WiBotic, are developing a charging solution that can satisfy these needs. The performance and specifications of the proposed wireless charging system are summarized as follows:

  • Dust tolerant design for 1 µm lunar regolith particles
  • Charging rate of 1-1.5 kW
  • Charging range of 0-4cm (horizontal spacing), +/-5cm (lateral misalignment), 0-70deg (angular misalignment)
  • Mass of 10kg
  • Compact base station size of 29 x 37 x 33 cm and power receiver size of 12 x 18 x 3 cm
  • Operational temperature range of -200C to +86C to enable operations at the lunar pole and equator
Potential NASA Applications (Limit 1500 characters, approximately 150 words)

There are several applications that necessitate proximity chargers in space. In relation to the Moon, these activities include supporting marsupial roving missions, enabling robotic systems that do not contain onboard nuclear or solar power generators, charging toolkits on crewed lunar terrain vehicles, and powering the heaters of critical devices to survive the lunar night. Near-field wireless power transmitters are important tools to reduce regolith incursion in mechanically mated systems and static joints.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Robotic systems are increasingly utilized in warehouses, energy/utility plants, construction sites, mines, and for last mile delivery applications. Underwater robotic systems enable ocean research for aquaculture, ocean mapping and maritime trade security inspections. All of these systems are battery powered and require recharging to maintain a high level of reliability and automation.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z4.04-5436
SUBTOPIC TITLE:
 Real Time Defect Detection, Identification and Correction in Wire-Feed Additive Manufacturing Processes
PROPOSAL TITLE:
 Real-Time Optical Defect Detection, Identification and Correction Technology
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Intellisense Systems, Inc.
21041 West Western Avenue
Torrance, CA 90501
(310) 320-1827

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Halina Tran
E-mail:
eos@intellisenseinc.com
Address:
21041 S. Western Ave. Torrance, CA 90501 - 1727
Phone:
(310) 320-1827

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Frank Willis
E-mail:
notify@intellisenseinc.com
Address:
21041 S. Western Ave. Torrance, CA 90501 - 1727
Phone:
(310) 320-1827
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Intellisense Systems, Inc. proposes to develop a new Real-Time Optical Defect Detection, Identification and Correction (ODIN) technology for wire-feed additive manufacturing (AM) based on a multi-sensor approach combined with a defect-correction algorithm. The ODIN system will enhance NASA’s current AM capability for space applications and structure reliability monitoring. The ODIN system consists of two underlying technological modules: (1) the sensor module, which combines optical high-resolution spatial mapping, an IR camera for thermal mapping, and a wire-feed speed monitor for nozzle clogging detection; and (2) the defect detection, identification and correction software module, which creates a surface from the point cloud of each printed layer, compares it to the CAD model of the part, determines location, volume and type of defect and creates new printing instructions to correct detected printing defects. The innovations of ODIN include the use of a structured light COTS 3D scanner for detection of spatial defects, a miniature IR camera to monitor part temperature, and an optical encoder of wire-feed speed to detect nozzle clogging to cover virtually all causes for printing defects and correct them in real time. To identify and correct spatial defects, the surface point cloud of the printed part is compared to the corresponding sections of the part’s CAD model in real time for feedback control. These monitoring methods target a broad range of defect types that can be captured immediately. In addition, when a discrepancy above the user-specified threshold level is detected at a certain location, ODIN computes additional 3D printing steps necessary to correct the defect. Material testing will be performed to estimate the impact of real-time print correction on the parts’ mechanical properties. This novel development will significantly reduce the need for post-build full part inspection and re-printing in case of inferior part quality.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The ODIN system will enhance NASA’s current AM capability for space applications and structure reliability monitoring. In particular, real-time feedback loop monitoring of the printing process and on the fly printing defect correction are an integral and critical element in NASA’s effort to substantially reduce post-print part inspection and costly re-prints of compromised parts.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

As a fully integrated and automated real-time AM monitoring and correction system, ODIN will find a plethora of applications where part inspection and printing of complex structures or material systems are needed by industrial customers such as aircraft or automobile part manufacturing and part inspection.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z5.04-6352
SUBTOPIC TITLE:
 Technologies for Intra-Vehicular Activity Robotics
PROPOSAL TITLE:
 PLUMMRS: A collection of Plan Ledgers and Unified Maps for Multi-Robot Safety
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
TRACLabs, Inc.
100 North East Loop 410, Suite 520
San Antonio, TX 78216
(281) 461-7886

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Ana Huaman Quispe
E-mail:
ana@traclabs.com
Address:
16969 North Texas Avenue, Suite 300 Webster, TX 77598 - 4085
Phone:
(404) 202-4843

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
David Kortenkamp
E-mail:
korten@traclabs.com
Address:
100 North East Loop 410, Suite 520 San Antonio, TX 78216 - 1234
Phone:
(281) 461-7886
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

One major hurdle to robust multi-robot operations in space is the same hurdle faced by multi-robot applications on Earth—co-located, yet independent, robotic "individuals" do not adequately share state information. State information can include: environmental knowledge, current position and velocity, future state estimates, what task is currently being performed, what resources are needed to complete the current task, where shared resources may be located, and even data about if/why execution failed. Sharing some amount of state information is not only a necessity for multi-robot tasks that require cooperation, but is critical even for groups of independent robots that must share resources.

TRACLabs proposes to create a collection of software processes, called PLUMMRS, that will facilitate sharing of environmental and internal state information to enable safe, efficient navigation and manipulation tasks by heterogeneous robot teams working in a shared workspace. The goal of PLUMMRS (Plan Ledgers and Unified Maps for Multi-Robot Safety) is to provide simple APIs for existing single-agent planning and execution systems to leverage—allowing them to be safely used in multi-agent contexts. PLUMMRS can be used by any individual robot in a group of robots to contribute to, and benefit from, a unified model of not only geometric and semantic perception data but also of expected and currently executing motion- and task-level plan data. PLUMMRS is not a planning framework, as each robot is expected to have its own "black-box" motion- and task-planning capabilities; however, PLUMMRS can be used by both motion- and task-planning & control systems as 1) an oracle of shared knowledge, 2) a safety monitoring watchdog based on shared knowledge, and 3) an arbiter (scheduler) that attempts to loosely coordinate the short-term and long-term desires proposed by all robots that are trying to independently complete their tasks while sharing a workspace and physical resources.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

A variety of NASA missions could benefit from PLUMMRS for multi-robot teaming, including ISS robots like Astrobee and R2, the Lunar Gateway, OSAM systems like Restore-L, the in-Space Assembled Telescope, Orbital Debris Mitigation, Artemis, the Lunar Surface Science Mobility System, Commercial Lunar Payload Services, Mars sample return, Discovery, exploration mission opportunities like Titan or Europa, swarm-based exploration of Mars lava tubes, and various STMD technology demonstrations.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The DoD needs robot teams for space, air, land, and sea. Relevant parties include the Air Force Space and Missile Systems Center, AFRL RANGRS, U.S. Army TARDEC, the Combating Terrorism Technical Support Office, the Naval Aviation Enterprise, and the Army Futures Command.

TRACLabs' customers in aerospace, automotive, and oil & gas manufacturing are also using robot teams for assembly and inspection.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z8.10-6501
SUBTOPIC TITLE:
 Wireless Communication for Avionics and Sensors for Space Applications
PROPOSAL TITLE:
 An Intelligent Wireless Instrumentation Network (I-WIN) for Space Applications
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Modularity Space
1511 Aviation Center Parkway
Daytona Beach, FL 32114
(386) 281-6753

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ms. Madison Mangano
E-mail:
contact@modularityspace.com
Address:
1511 Aviation Center PKWY Daytona Beach, FL 32114 - 5723
Phone:
(631) 338-8617

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Scott Weintraub
E-mail:
scottw@modularityspace.com
Address:
2911 Sime Street New Smyrna Beach, FL 32168 - 2435
Phone:
(386) 987-8847
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 6
Technical Abstract (Limit 2000 characters, approximately 200 words)

Modularity Space proposes an innovative software and hardware package for an Intelligent Wireless Instrumentation Network Framework (I-WIN). I-WIN revolves around a plug-and-play framework and to enable a network-centric communications link for avionics and sensor components. This software architecture, coupled with highly configurable and advanced manufactured embedded hardware, develops a system focused on interoperability between subsystems and sensors and avionics applications. I-WIN provides an adaptable and modular architecture for innovative avionics, transforming both current and future satellite systems into wireless component networks (WCN). These WCNs can be configured at run-time reducing systems engineering costs, data distribution complexities, and enables the use of commercial-off-the-shelf components. Using Intelligent Wireless Modules (IWM), the self-configuring architecture is enabled without the use of predefined configurations of the components. I-WIN and IWMs provide an inherent fault tolerance and dynamic fault management system coupled with a low size, weight, and power (Low-SWaP) sensing solution for spacecraft. The packaged solution will be developed, and preliminarily evaluated during this Phase I research effort using software and hardware-in-the-loop setups available for this project. The proposed solutions will be capable of augmenting existing early stage mission architectures increasing autonomy and reliability and will also provide a baseline for a wireless spacecraft avionics for future space missions and operations.

 

I-WIN will provide a theoretical and experimental framework for development and demonstration of wireless technologies to increase space system capabilities, reduce integration and design complexities, and produce a rapid response avionics package capable of using advanced manufacturing techniques. The successful completion of this Phase I effort will take the technology from a TRL 3 to a TRL 6. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

This list represents a subset of potential applications

  • NASA robotic rovers, satellites, deep space systems, and lunar landers vehicles
  • Modular wireless avionics kits for NASA spacecraft development
  • Payload integration services on ISS through wireless payload platforms
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

This list represents a subset of potential applications

  • Wireless networks for commercial terrestrial vehicles (UAV, autonomous cars, etc)
  • Independent, Low-SWaP, wireless plug-and-play modules for varying industry domains
  • Commercial on-orbit service space systems for rapidly developed, low-cost services
Duration: 6

PROPOSAL NUMBER:
 20-1- H5.01-5543
SUBTOPIC TITLE:
 Lunar Surface Solar Array Structures
PROPOSAL TITLE:
 Self-Erecting Elevated Platform
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
TentGuild Engineering Company
4740 Table Mesa Drive
Boulder, CO 80305
(866) 666-7761

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Gyula Greschik
E-mail:
greschik@teguec.com
Address:
4740 Table Mesa Drive Boulder, CO 80305 - 4505
Phone:
(866) 666-7761

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Gyula Greschik
E-mail:
greschik@teguec.com
Address:
4740 Table Mesa Drive Boulder, CO 80305 - 4505
Phone:
(866) 666-7761
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Proposed is a portable guyed lattice column system with an erector mechanism to autonomously lift and uphold a payload, such as a solar array that needs to be elevated to provide continuous power near a Lunar pole.  Deployment proceeds from the base up, bay by bay, as the erector jacks each bay open while rising with the mast top where the bays yet to be opened are also stacked.  The guy wires are sequentially tightened as deployment proceeds.  Thus, full strength and stiffness are guaranteed for the mast sections already extended.  Reverse operation collapses the column.  

The system is eminently scalable and adaptable.  Even with a fixed mast design, the number of bays and the anchoring geometry can be easily set to serve any of a variety of platform heights and payload weights.

Developed are a conceptual design ready for hardware development for the mast-and-erector assembly, and a procedure to assist preliminary design for autonomous Lunar applications. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Lightweight, modular, repeatedly deployable, and autonomously operable elevated platforms to raise and uphold solar arrays for Lunar missions in the polar regions, or to lift and support above the planetary surface instruments or equipment for other extraterrestrial applications.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Light weight guyed tower structures for environments or time constraints that forbid traditional erection methods (hoisting, cranes, or helicopters).  This includes meteorological/research and military use.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z2.01-5687
SUBTOPIC TITLE:
 Spacecraft Thermal Management
PROPOSAL TITLE:
 A SINDA-Compatible Human Thermal Model for Assessing Crew-Induced Loads
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
ThermoAnalytics, Inc.
23440 Airpark Boulevard
Calumet, MI 49913
(906) 482-9560

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Allen Curran
E-mail:
arc@thermoanalytics.com
Address:
23440 Airpark Blvd Calumet, MI 49913 - 9233
Phone:
(906) 281-1390

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Kevin Denomme
E-mail:
kdd@thermoanalytics.com
Address:
23440 Airpark Blvd Calumet, MI 49913 - 9233
Phone:
(906) 482-9560
Estimated Technology Readiness Level (TRL) :
Begin: 4
End: 7
Technical Abstract (Limit 2000 characters, approximately 200 words)

The objective of the proposed research is to create a state-of-the-art, human thermal model that predicts crew member induced loads for evaluating a (long-distance) exploration vehicle’s thermal control, environmental control, and life support systems, including for conceptual and early design modeling. To accomplish this, ThermoAnalytics will adapt its widely-used, actively-developed, commercial-off-the-shelf Human Thermal Model for use with the Systems Improved Numerical Differencing Analyzer (SINDA). Specifically, we will create an interface between the TAITherm HTM and Thermal Desktop, which is a front-end to SINDA. The resulting co-simulation will provide conjugate assessments of crew-induced loads and vehicle thermal control systems, predicting the human crew’s (HTM) requirements of the exploration vehicle (TD) as they produce heat, moisture, and gasses (CO2) and consume O2.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed research will be targeted for use by the NASA Crew and Thermal Systems Division for simulation of Life Support Systems during long duration missions. This includes Environmental Control Systems thermal performance studies, which can be limited by moisture under extreme conditions. Other potential NASA applications are improved modeling and testing of EVA spacesuit technology and the simulation of cooling vests or wearable electronics that have unique challenges due to the interaction with the human thermoregulatory system.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The US DoD (Army Natick Soldier Center, Navy SOCOM) is interested in simulating the thermal effects of high activity levels and the impact of sweat and moisture transport on clothing system insulation. For commercial customers, simulation of high activity levels is of interest for sportswear and advanced textile companies (i.e., W.L. Gore, Nike) and wearable electronics manufacturers.

Duration: 6

PROPOSAL NUMBER:
 20-1- H4.05-6156
SUBTOPIC TITLE:
 Liquid Cooling and Ventilation Garment Connector Upgrade and Glove Humidity Reduction
PROPOSAL TITLE:
 Single-Piece Leak Mitigating Water Loop Connector
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Mainstream Engineering Corporation
200 Yellow Place
Rockledge, FL 32955
(321) 631-3550

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ian Wright
E-mail:
iwright@mainstream-engr.com
Address:
200 Yellow Place Rockledge, FL 32955 - 5327
Phone:
(321) 631-3550

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Michael Rizzo
E-mail:
mar@mainstream-engr.com
Address:
200 Yellow Place Rockledge, FL 32955 - 5327
Phone:
(321) 631-3550
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

NASA is currently seeking upgrades for the current extra-vehicular mobility unit (EMU). The water connector for the liquid cooling and ventilation garment (LCVG) has been shown to be a point of potential failures for the exploration space suit. Mainstream proposes to develop an upgraded water connector that eliminates leakage, performs over long-term cycling, and maintains strict water quality levels. In Phase I, Mainstream will design, prototype, and test an upgraded LCVG water connector, and will perform water contaminant studies. In Phase II, Mainstream will finalize the manufacturing technique and perform all reliability, life, and space-readiness tests.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed research is targeted at existing and next generation Liquid Cooling and Ventilation Garments. Future missions will require demanding extra vehicular activities on the international space station, moon, and mars. Our technology mitigates the concern of leakage from the LCVG water loop connector, a primary design concern for the existing system.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Innovative liquid cooling garments are useful in any working environment where the worker is enclosed in a protective suit. One example use is with firefighting PPE. With this technology, firefighters will be able to face extreme conditions for longer periods of time. Other potential PPE commercial markets include hazmat cleanup crews, paint booth workers, automotive racing, and soldiers.

Duration: 6

PROPOSAL NUMBER:
 20-1- H12.01-6490
SUBTOPIC TITLE:
 Radioprotectors and Mitigators of Space Radiation-induced Health Risks
PROPOSAL TITLE:
 C60-Serinol to Alleviate the Consequences of Cosmic Radiation
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
AGNI Medical LLC
10961 Burnt Mill Road, Unit 237
Jacksonville, FL 32256
(904) 351-8478

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Elena Vishnyakova
E-mail:
nanoreactor2018@gmail.com
Address:
10961 Burnt Mill Rd. Unit 237 Jacksonville, FL 32256 - 4676
Phone:
(904) 351-8478

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Elena Vishnyakova
E-mail:
nanoreactor2018@gmail.com
Address:
10961 Burnt Mill Rd. Unit 237 Jacksonville, FL 32256 - 4676
Phone:
(904) 351-8478
Estimated Technology Readiness Level (TRL) :
Begin: 4
End: 6
Technical Abstract (Limit 2000 characters, approximately 200 words)

Astronauts on long term space missions incur multiple space radiation risks including cancer, late and early central nervous system effects, cardiovascular diseases, and accelerated aging. A common mechanistic pathway in these events is unchecked oxidative stress. We have developed a countermeasure that protects mice from whole body x-ray radiation-induced death when given systemically 4 hours after lethal radiation exposure. At this time point, a lot of the immediate free radical generation from ionizing radiation exposure has already occurred and yet, we were able to protect these mice. This is largely due to the extremely potent free radical scavenging ability of our C60 fullerene derivative we term C60-ser that (i) has been made biocompatible by decorating it with a serinol malonamide to dramatically increase its water solubility (>250 mg/ml) and (ii) readily traverses physical barriers within tissues and cells to achieve excellent concentrations in all tissues within the body. C60-ser exists in a dynamic equilibrium state seamlessly flipping between the conjugate monomers (~3nm) and aggregates (100-2000 nm). Such duality enables the conjugates to use passive diffusion and active transport (e.g. endocytosis, transcytosis) for efficient and seamless shuttling from the vasculature to tissues including the brain. The sub-5nm size also allows a long circulation time by evading opsonization and reticuloendothelial capture and facilitating renal elimination. C60-ser can be reliably and reproducibly created in our facilities by facile and scalable techniques that we have pioneered. The studies proposed in this submission are extensions of this exciting preliminary work that will now explore the ability of C60-ser to protect multiple cell types from charged particle radiotherapy injuries.  Collectively these studies will set the stage for testing C60-ser in animal models in phase II of this NASA SBIR program.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

We have developed a radiation countermeasure, C60-ser, that protects mice from whole body x-ray radiation-induced death when given systemically 4 hours after lethal radiation exposure. If these properties hold true with space exposure-relevant radiation types, energies, and doses, we expect C60-ser could be used by astronauts during space missions (prophylactically before take-off or therapeutically after documented high-risk exposure such as a solar flare event).

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Our radiation countermeasure, C60-ser, protects mice from whole body x-ray radiation-induced death when given systemically 4 hours after radiation via extremely potent free radical scavenging. This ability could make it valuable as a radiation protector during cancer radiotherapy and/or as a radiation mitigator following incidental radiation exposure from nuclear accidents or bioterrorism.

Duration: 6

PROPOSAL NUMBER:
 20-1- S4.02-4708
SUBTOPIC TITLE:
 Robotic Mobility, Manipulation and Sampling
PROPOSAL TITLE:
 Lunar Automatic Tool Changer and Holder (LATCH)
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Motiv Space Systems, Inc.
350 North Halstead Street
Pasadena, CA 91107
(626) 737-5988

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Richard Fleischner
E-mail:
richard.fleischner@motivss.com
Address:
350 North Halstead Street Pasadena, CA 91107 - 3122
Phone:
(626) 737-5991

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Tom McCarthy
E-mail:
tom.mccarthy@motivss.com
Address:
350 North Halstead Street Pasadena, CA 91107 - 3122
Phone:
(626) 389-5783
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Motiv Space Systems, Inc. ("Motiv") is proposing a new design for a contamination tolerant tool-changer for use on lunar and other off-Earth missions that employ a robotic arm with a modest complexity end-effector payload (i.e., not an MSL-class payload). Past missions such as Phoenix and InSight are examples of missions with robotic arms that in retrospect could accommodate such a tool-changer. Future missions with a similar class of robotic arms include the lunar COLDArm, a Technology Payload for the Commercial Lunar Payload Services (CLPS) suite of mission opportunities, and exploratory missions to the surfaces of the Ocean Worlds, comets, and asteroids. For these missions, a tool-changer would enable the robotic arm to perform a more complicated suite of activities such as scooping, gripping, grinding, and debris removal, all using separate tools that are swapped onto the arm as needed. This SBIR addresses a major problem with tool-changing mechanism designs in general, in that they are comprised of mechanical and electrical coupling elements that are sensitive to contamination. Contamination can result in failure to couple or jamming upon release, along with intermittent or broken electrical continuity. Because robotic arm end-effectors are likely to interact with the surface (and subsurface) of the Moon, Mars, or other planetary bodies, contamination problems are inevitable, the Moon in particular because the regolith particles are small, sharp, and prone to attachment because of the Moon's static electricity buildup. Motiv's tool-changer design will allow contamination to collect on mechanical and electrical coupling features and surfaces, but not preclude normal functioning of the tool-changer beyond some loss of positional repeatability when the various tools are exchanged. Electrical functionality will be preserved via self-cleaning of the electrical contacts during the tool exchange cycles

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Potential applications for the contamination tolerant tool changer are missions with in-situ robotic arm activities in which the arm requires end-effector tools or instrumentation of modest complexity, particularly regarding electrical signal count. These missions would benefit from the additional flexibility that exchangeable tools offers. The contamination tolerance of the design would allow for its use on the Moon, Mars, the Ocean Worlds, comets, and asteroids, all of which are known to have environments rich in contaminating particulates.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

A contamination tolerant tool-changer would be a useful part of terrestrial robotic arm systems, particularly those incorporated into mobile robotic platforms that perform hazardous duties or serve in hazardous environments. Tool exchange flexibility and worn or malfunctioning tool replacement would mitigate the time needed for human interaction, expanding uninterrupted service time

Duration: 6

PROPOSAL NUMBER:
 20-1- S2.03-4788
SUBTOPIC TITLE:
 Advanced Optical Systems and Fabrication/Testing/Control Technologies for EUV/Optical and IR Telescope
PROPOSAL TITLE:
 Laser Machining
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
OptiPro Systems, LLC
6368 Dean Parkway
Ontario, NY 14519
(585) 265-0160

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
James Munro
E-mail:
JMunro@optipro.com
Address:
6368 Dean Parkway Ontario, NY 14519 - 8970
Phone:
(585) 265-0160

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Matt Carlson
E-mail:
mcarlson@optipro.com
Address:
6368 Dean Parkway Ontario, NY 14519 - 8970
Phone:
(585) 265-0160
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Several presentations were given at NASA’s 2019 Mirror Tech Days that highlighted the shortcomings of current mirror-fabrication technologies, particularly as they relate to demanding missions such as LUVOIR and HabEx.  Many of the mirror deficiencies, such as areal density, surface figure error, stiffness, and surface figure changes over temperature, can be traced – either directly or indirectly – to mirror lightweighting.  Current lightweighting processes result in pockets in the rear-side of the mirror that have abrupt stress-concentrating corners, poor front-rear symmetry, and poor material allocation in the webbing.  The proposed laser machining process allows for the fabrication of cavities within a mirror that preserves front-rear symmetry, has no corners, and has a near ideal allocation of material within the webbing.

The novel laser machining process utilizes a CO2 laser in an ablation regimen in which the focused beam strikes below the surface of the workpiece from the side (as opposed to the front or rear as is commonly done).  Material between the focused beam and the surface is ejected by the shockwave produced by the laser’s pulse, greatly increasing the amount of material removed for each pulse.  Further, the focused laser beam can be split in two and laterally separated; when pulsed the shockwave – and material removal – can bridge the gap between the focal spots and increase the removal rate further.  We project that material removal rates exceeding 80 cubic millimeters per second are possible.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

1. Lightweighting of astronomical mirrors and mirror segments.

2. Coarse grinding of optical prescriptions into the front surface of astronomical mirrors and mirror segments.

3. Coarse grinding of the rear side of astronomical mirrors and mirror segments.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

1. Grinding prescriptions into the front and rear surface of optical components 

2. Coarse grinding ceramic components to their near-net-shape.

Duration: 6

PROPOSAL NUMBER:
 20-1- A1.08-4810
SUBTOPIC TITLE:
 Aeronautics Ground Test and Measurement Technologies
PROPOSAL TITLE:
 Global Skin Friction Sensor for Cryogenic Wind Tunnels
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Innovative Scientific Solutions, Inc.
7610 McEwen Road
Dayton, OH 45459
(937) 429-4980

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Jim Crafton
E-mail:
jwcrafton@innssi.com
Address:
7610 McEwen Road Dayton, OH 45459 - 3908
Phone:
(937) 630-3012

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Larry Goss
E-mail:
gosslp@innssi.com
Address:
7610 McEwen Road Dayton, OH 45459 - 3908
Phone:
(937) 429-4980
Estimated Technology Readiness Level (TRL) :
Begin: 5
End: 6
Technical Abstract (Limit 2000 characters, approximately 200 words)

While skin friction is a key parameter for characterizing fluid flows, it has proven to be a difficult quantity to measure. Currently, skin friction is measured at discrete locations using different sensors; however, determining the proper measurement locations a priori is a significant challenge. Measurement techniques that provide global distributions of skin friction, such as oil film interferometry, shear sensitive liquid crystals, and surface stress sensitive films, have demonstrated steady state skin friction distributions in specific settings. Unfortunately, deployment of these measurement techniques into cryogenic wind tunnels has proven difficult. A system that can provide global measurements of mean and unsteady skin friction is of significant interest. ISSI and WMU propose exploiting existing measurement systems for temperature and utilizing a new variational mathematical approach that can extract global skin friction from high spatial resolution distributions of surface temperature acquired using Temperature-Sensitive Paint (TSP) and IR thermography. The process is based on the well-established relationship between the energy equation and skin friction. This approach has recently been demonstrated by the proposing team as part of a Phase II Air Force SBIR program, thus demonstrating the technical maturity of the technique. Temperature-Sensitive Paint and IR thermography are high TRL tools that are currently used in wind tunnels at both room temperature and cryogenic conditions. These systems, combined with surface heating devices such as carbon nanotubes, provide the high spatial resolution measurements of temperature gradients that are required for extraction of skin friction using this new approach. Combining the proven measurement capabilities of TSP and IR thermography with this new variational approach to extraction of skin friction results in a low risk approach to providing global skin friction measurements in cryogenic wind tunnels.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The SFW program has developed a model to assess the capabilities of various computational techniques, FAITH Hill. Fluctuating aerodynamic loads are a significant concern for the SLS program as unsteady aerodynamic pressures can excite the vehicle dynamic modes. Experimental measurements from the proposed sensor would provide each of these programs with heat transfer and flow separation/attachment data to validate computational models. Similar testing capability could be demonstrated in other NASA tunnels as part of a Phase II program.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The final product from this program should be a system capable of acquiring high spatial resolution distributions of both heat transfer and skin friction on a model in a cryogenic wind tunnel. This is a technological capability that is of interest to ISSI’s current commercial, research, and military wind tunnel customers. ISSI expects to aggressively market this capability to these customers.

Duration: 6

PROPOSAL NUMBER:
 20-1- S2.02-5072
SUBTOPIC TITLE:
 Precision Deployable Optical Structures and Metrology
PROPOSAL TITLE:
 Precision Femtosecond Laser Additive Manufacturing and Athermal Welding
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Polaronyx, Inc.
2526 Qume Drive, Suites 17 and 18
San Jose, CA 95131
(408) 573-0930

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Shuang Bai
E-mail:
sbai@polaronyx.com
Address:
2526 Qume Drive, Suites 17 and 18 San Jose, CA 95131 - 1870
Phone:
(408) 573-0930

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Jian Liu
E-mail:
jianliu@polaronyx.com
Address:
2526 Qume Drive, Suites 17 and 18 San Jose, CA 95131 - 1870
Phone:
(408) 573-0930
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

This NASA SBIR Phase I proposal presents an unprecedented precision laser 3D manufacturing system including additive manufacturing, subtractive manufacturing and athermal welding, by using a pulsed fiber laser and real time sensing and feedback control. It is the enabling technology for manufacturing high precision telescope structures with sub-micron precision. With our successful history in laser 3D manufacturing, this proposal has a great potential to succeed. A proof of concept demonstration will be carried out and samples will be delivered at the end of Phase 1. Prototypes in compliant with the NASA large telescope system requirement will be delivered at the end of Phase II.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

In addition to NASA’s telescope components manufacturing, the proposed pulsed laser 3D manufacturing process can also be used in other applications, such as space vehicle, aircraft, and satellite manufacturing. PolarOnyx will develop a series of products to meet various requirements for commercial/military deployments.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)
  • 3D printing uses various technologies for building the products for all kinds of applications from foods, toys to rockets and cars. The global market is projected to reach US$44 billion by the year 2025.
  • Medical devices and biomedical instrumentation that consists of surgical and infection control devices, general medical devices, cardiovascular, home healthcare, and other devices.
Duration: 6

PROPOSAL NUMBER:
 20-1- H12.05-5829
SUBTOPIC TITLE:
 Autonomous Medical Operations
PROPOSAL TITLE:
 Monitoring, Learning and Optimizing Crew Health and Performance
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Exploration Institute, LLC
710 North Post Oak Road, #400
Houston, TX 77024
(617) 599-0774

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Michael Mercury
E-mail:
michael@explorationinstitute.com
Address:
710 North Post Oak Road #400 Houston, TX 77024
Phone:
(626) 269-8248

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Armin Ellis
E-mail:
ate@explorationinstitute.com
Address:
710 North Post Oak Road #400 Houston, TX 77024 - 1111
Phone:
(617) 599-0774
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

 

We propose to develop and demonstrate an artificial intelligence / machine learning (ML) algorithm which will reveal insights into astronaut health and performance, which in turn can be used to reduce mission risk, and optimize spacecraft resources and limited astronaut time during the mission. The proposed ML algorithm can be applied to any astronaut biometric data including heart rate, blood oxygen, temperature, nutrition in consumed food, environmental control system parameters, and injury and illness reports to better inform astronauts and the Mission Control Center with actionable insights made available in real time. Patterns in these data can indicate that astronauts are not at peak physical or mental performance, and patterns in these data sets can suggest how to return the astronauts to peak performance.

This algorithm can provide critical insights to astronauts by recognizing subtle patterns that appear across many telemetry channels. For example, this algorithm could track metabolic activity in crew in real time and suggest changes to environmental system parameters to maintain constant CO2 levels in a most resource-efficient way. Another example is early warning of dangerous conditions (precursors to hypercapnia). Its diagnostic power lies in its ability to learn in real time, and also in its ability to find subtle correlations between multiple bio parameters in data telemetry available to it. This algorithm also has the added benefit of fast learning for adapting to nuances between astronauts' metabolic profiles and finding new diagnostic correlations in real time during the mission.

As NASA sends crew out to the Moon and beyond to deep space and Mars, the lack of a quick return to Earth means early diagnosis of physical and mental health problems could mean the difference between life and death. This algorithm is compatible with low power hardware so it can be performed onboard spacecraft in deep space where there is limited data connectivity to Earth.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

This product is directly applicable to future crewed NASA missions that are at the Moon or beyond where there is less opportunity for a quick return to Earth. In these cases biomarker monitoring can provide early warning for health concerns needing attention. In these cases also resources are even more precious and the product can help optimize use of those limited resources. Our proposed innovation works with any time series data available, such as that provided by the International Space Station (ISS) Food Intake Tracker (ISS FIT) iPad App.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Personalized monitoring and tracking precursors for optimal performance and health applied to the following markets:

  • Commercial Spaceflight: Space tourism and commercial astronauts
  • Extreme Performance: Athletes, war-fighters, first responders, commercial and recreational pilots
  • Consumer products: Individual health tracking, hospital patients, child and elderly monitoring
Duration: 6

PROPOSAL NUMBER:
 20-1- S5.01-4746
SUBTOPIC TITLE:
 Technologies for Large-Scale Numerical Simulation
PROPOSAL TITLE:
 Technologies for Large-Scale Numerical Simulation
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
WarpIV Technologies, Inc.
5230 Carroll Canyon Road, Suite 306
San Diego, CA 92121
(858) 605-1646

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Jeffrey Steinman Ph.D
E-mail:
jeffrey.steinman@warpiv.com
Address:
5230 Carroll Canyon Road, Suite 306 San Diego, CA 92121 - 2016
Phone:
(858) 531-0643

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Teresa Hernandez
E-mail:
teresa.hernandez@warpiv.com
Address:
5230 Carroll Canyon Road, Suite 306 San Diego, CA 92121 - 2016
Phone:
(858) 605-1646
Estimated Technology Readiness Level (TRL) :
Begin: 4
End: 7
Technical Abstract (Limit 2000 characters, approximately 200 words)

This proposal demonstrates how the parallel discrete-event simulation technology of the WarpIV Kernel can be used to effectively solve large-scale numerical simulations related to NASA problems. Four diverse applications will be demonstrated: (1) modeling planetary rings as an N-body gravitational system, (2) modeling space debris and possible collisions with satellites or rocket launches, (3) modeling RF propagation for monitoring weak spacecraft signal strengths in noisy RF environments, and (4) producing non-spherical high-resolution gravity models. The most important of these demonstrations is the planetary ring model that was originally proposed by Dr. Steinman at the Jet Propulsion Laboratory in 1995 prior to the launch of the Cassini mission. This proposal shows how N-body gravitational models can achieve orders of magnitude improvements to performance using discrete-event techniques (as opposed to time stepped techniques) while also producing more accurate results.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

All high-performance computing science applications. This proposal lists four applications that will be demonstrated: (1) modeling planetary rings as an N-body gravitational system, (2) modeling space debris, (3) modeling RF propagation for monitoring spacecraft signal strengths in noisy RF environments, and (4) producing non-spherical high-resolution gravity models. The discrete-event approach could easily apply to a variety of CFD applications.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The large-scale numerical simulation capabilities that will be demonstrated in this effort naturally extend to all HPC simulation applications. In particular, this effort demonstrates how discrete-event approach (vs. time stepping) not only facilitates orders of magnitude faster executions, but also produces more accurate results.

Duration: 6

PROPOSAL NUMBER:
 20-1- A1.04-5492
SUBTOPIC TITLE:
 Electrified Aircraft Propulsion
PROPOSAL TITLE:
 Distributed Inverter Array Turn-Less Motor
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Polarix Corporation
7960 Silverton Avenue, Suite 119
San Diego, CA 92126
(202) 812-0088

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Oved Zucker
E-mail:
oved.zucker@polarixcorp.com
Address:
7960 Silverton Avenue Suite 119 San Diego, CA 92126 - 6340
Phone:
(703) 901-5340

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Farida Lim
E-mail:
farida.lim@polarixcorp.com
Address:
6829 Little River Turnpike Annandale, VA 22003 - 3558
Phone:
(202) 812-0088
Estimated Technology Readiness Level (TRL) :
Begin: 4
End: 7
Technical Abstract (Limit 2000 characters, approximately 200 words)

The performance parameters of electric motors for aviation propulsion are: 1) specific power (SP), 2) reliability, and 3) efficiency.  The Polarix ACTS motor provides a substantial enhancement of all three. This is the result of a new motor topology made possible by the integration of the inverter with the electro-mechanical current carrying elements.  The topology has the following unique characteristics:  1) elemental motors distributed around the periphery, each with its independently controlled inverter with overall control from a master MCU, 2) the elemental motors contained by 3 conductors with a dedicated inverter at one end, and a short at the other and thus no turns, and 3) the planar arrangement of the conductors allows for MEMS type manufacturing.

 

This topology results in almost halving the volume and weight of the magnetic circuit and thus effectively doubling the specific power.  Secondly, the large independent motor elements provide for massive redundancy and thus substantial higher reliability.  Also, the elimination of turns and external wiring allows for greater copper utilization and thus higher efficiency. 

 

The performance discussed in the proposal in parametric form (Figure 9) shows 30kW/kg specific power with stator cooling at 5W/cm2 at 99% efficiency excluding windage and core losses.

 

The state of the art includes both the motor and the inverter.  We have built a number of motors with construction performance required for the proposed motor and likewise we have built numerous inverters and have tested the required currents voltage and power.

 

The program proposed here will integrate the various elements already demonstrated into a motor with power exceeding 50kW and specific power exceeding 10kW/kg and projected at 15W/kg.

 

We project that the phase II will demonstrate a motor in the 500kW range and with SP power above 20kW/kg.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Applications include airborne propulsion applications - manned and unmanned, covering the power range from 1kW to MWs of hub motors for driving propellers and rim motors driving fans. The latter will have a major impact on hybrid airplanes and the development of more advanced jet engine which will now have the ‘electric gearbox’ as part of the engine system.   The motor will see applications in various aviation applications such as flight control actuator and many other electromechanical control and actuation of various subsystems.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Its unique characteristics of the Polarix ACTS motor are its very high specific power, light weight, high reliability, high efficiency and a low cost.  These features lend it to a broad range of commercial applications, terrestrial marine and airborne applications such as generators for APUs, marine/UAV, airborne UAV, and terrestrial vehicles.  

Duration: 6

PROPOSAL NUMBER:
 20-1- H5.02-4846
SUBTOPIC TITLE:
 Hot Structure Technology for Aerospace Vehicles
PROPOSAL TITLE:
 Formable Preform for Complex Shaped Hot Structures
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Pepin Associates
15 Log Home Rd
Greenville, ME 04441
(207) 695-3434

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. John Pepin
E-mail:
pepin@midmaine.com
Address:
15 Log Home Rd Greenville, ME 04441 - 0397
Phone:
(207) 695-3434

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. John Pepin
E-mail:
pepin@midmaine.com
Address:
15 Log Home Rd Greenville, ME 04441 - 0397
Phone:
(207) 695-3434
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

In this Phase I Program Pepin Associates extends its aligned discontinuous preform technology to hot structures.  Aligned discontinuous preforms allow complex preform shapes to be formed rapidly while retaining mechanical properties for efficient, lightweight structures.  This technology reduces the cost of fabricating complex, integrated polymer matrix precursor structures for ceramic matrix composites.  Coupled with advanced CMC processing technologies these tailored formable preforms offer the potential for affordable hot structures of complex shape.   Pepin Associates and its team fabricate test panels to compare the mechanical properties of 2D and 3D baseline continuous with 2D and 3D aligned discontinuous C/C-SiNC composite laminates.  Tension, interlaminar shear, and in plane shear tests are performed at room temperature and elevated temperature.   Pepin Associates further demonstrates the ability of the tailored formable preform to fabricate an integrated stiffened skin subcomponent.  This subcomponent employs selective 3D reinforcement in a formable preform.  Material inspections verify the quality of this precursor structure such that it could be further processed to yield a CMC integrated hot structure. The Phase I program forms the basis for Phase II development of more advanced integrated hot structure and qualification testing and analysis to support the design of affordable complex shaped hot structures to meet NASA requirements.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA applications for the aligned discontinuous preform technology include integrated hot structures such as stiffened aeroshells, control surfaces and their attachments, engine components, nozzle extensions and exit cones.  More integrated structures for precursor polymer matrix composites will allow greater design flexibility for hot structures.  Formable interior cavities would allow passive and active cooling of hot structures.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

DARPA and the Air Force are developing a hypersonic air breathing weapon concept (HAWC) and a tactical boost glide vehicle (TBG).  The Army is developing an ultrafast maneuverable long range missile launched from a ground platform.    The low cost integrated structures developed in this Phase I program will create more design/manufacturing flexibility for these DOD hypersonic programs.

Duration: 6

PROPOSAL NUMBER:
 20-1- S2.05-6522
SUBTOPIC TITLE:
 Technology for the Precision Radial Velocity Measurement Technique
PROPOSAL TITLE:
 Cascaded Arrayed Waveguide Gratings for High Resolution Integrated Photonic Spectrographs
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
New Integration Photonics
5301 Dorset Avenue
Chevy Chase, MD 20815
(301) 367-9297

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Yang Zhang
E-mail:
yzhangdd@terpmail.umd.edu
Address:
3420 Toledo Terrace, Apt 362 Hyattsville, MD 20782
Phone:
(240) 264-0840

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mario Dagenais
E-mail:
dage@ece.umd.edu
Address:
5301 Dorset Ave Chevy Chase, MD 20815 - 6629
Phone:
(301) 405-3684
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

We are proposing to develop an integrated photonic chip for implementing a cascaded arrayed waveguide gratings (AWG) spectrometers on a Si3N4/SiO2 platform for use in the detection of exoplanets based on Precision Radial Velocity (PRV) method. In Phase I of this proposal, an integrated high spectral resolving power (R~150,000), high throughput (~25%) AWG spectrometer with multiple fiber inputs for simultaneous calibration on a Si3N4/SiO2 platform is proposed, which will be followed by a Phase II proposal for designing a flat focal field AWG spectrometer, with the focal signals of all wavelengths of operation focusing along a straight line, and for designing a polarization insensitive AWG for measuring the optical spectra of the star and the planet. Integration on a chip reduces the size, the weight, the cost, and increases the stability of astronomical spectrographs. An external calibration sources, like Optical Frequency Combs (OFCs), can be coupled to the AWG spectrometers through the additional fiber inputs to provide the broad spectral coverage and long-term (years) stability needed for extreme PRV detection of exoplanets.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

A successful completion of Phases I and II would allow the Company to claim to have realized an integrated spectrometer. This would be a very compact instrument that can potentially be used in many NASA related projects. This can include missile defense, sensors, lidar, laser ranging, medical and health applications. The Company will pursue opportunities with NASA for infusion in future NASA missions (including exoplanet detection).

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

AWGs can be used to multiplex multiple channels on a single optical fiber at the transmitter and also be used to demultiplex them back into their individual channels at the receiver. AWGs are commonly used as optical multiplexers and demultiplexers in a Wavelength Division Multiplexed system. There are other areas of application such as signal processing, measurement, and sensing.

Duration: 6

PROPOSAL NUMBER:
 20-1- H5.01-6530
SUBTOPIC TITLE:
 Lunar Surface Solar Array Structures
PROPOSAL TITLE:
 Articulating Airbeam Tripod Boom for Solar Arrays
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Ryzing Technoloties LLC
162A Greenville Avenue
Staunton, VA 24401
(540) 487-7881

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ryan Gundling
E-mail:
ryan.gundling@ryzingtech.com
Address:
162A Greenville Avenue Staunton, VA 24401 - 2440
Phone:
(540) 294-2928

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ryan Gundling
E-mail:
ryan.gundling@ryzingtech.com
Address:
162A Greenville Avenue Staunton, VA 24401 - 2440
Phone:
(540) 294-2928
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

The Articulating Airbeam Tripod Boom for Solar Arrays effort outlined here aims to provide a rapidly deployable structure that can support and elevate solar panel arrays for use in the Artemis Program's development of a long-term facility on the Lunar south pole. This textile-based structure will feature protective coatings and no rigid/mechanical components to prevent the negative impacts of Lunar dust. The packable solution will be easily moved and redeployed numerous times to allow for localized power and adaptable functionality for Lunar surface operations. 

Integrations with foldable solar arrays will help the Articulating Airbeam Tripod Boom for Solar Arrays fit into NASA priorities to use innovative materials and processes to create packable solutions that can deploy once on-site which saves valuable space during transport. Articulation features will maintain efficiency of solar arrays and an elevated height of 10m provides adaptability for use on the Moon.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA has expressed a specific interest in establishing a long-term presence on the Lunar South Pole because of its access to consistent sunlight. Powering this presence will require in-situ resource utilization along with portable adaptability. The Articulating Airbeam Tripod Boom for Solar Arrays provides a solution with minimal pack-volume to be easily moved to a location, re-packed moved and redeployed again multiple times. This will prove beneficial for other NASA surface missions anticipated for Mars and beyond.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Demand for portable solar arrays is expected to grow in the coming years, driven by military, outdoor adventure, off-grid living, field workers in remote locations, and disconnected or remote populations. Each of these end-users desire packable power solutions and the Articulating Airbeam Tripod Boom for Solar Arrays will be designed to adapt to the needs of these customers.

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.12-5255
SUBTOPIC TITLE:
 Remote Sensing Instrument Technologies for Heliophysics
PROPOSAL TITLE:
 Ocean Stabilized Ionospheric Remote Imaging Sensor (OSIRIS)
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Atmospheric & Space Technology Research Associates, LLC
282 Century Place, Suite 1000
Louisville, CO 80027
(303) 993-8993

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Irfan Azeem
E-mail:
iazeem@astraspace.net
Address:
5777 Central Avenue, Suite 221 Boulder, CO 80301 - 2829
Phone:
(303) 993-8039

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Rachel Hauser
E-mail:
rhauser@astraspace.net
Address:
282 Century Place Suite 1000 Louisville, CO 80027 - 1654
Phone:
(303) 993-8039
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

In this study, we propose to design an all-sky imaging system for ionospheric remote sensing from the surface of the ocean, which are currently not instrumented for space physics measurements. The proposed instrument, called Ocean Stabilized Ionospheric Remote Imaging Sensor (OSIRIS), will image the nightglow OI 630.0 nm emission data and will be capable of operating from mobile and moored buoys. The OSIRIS design solution will include a gimballed platform for sensor stabilization. The proposed OSIRIS instrument design is novel as ionospheric imaging from the ocean platform has not been demonstrated. We will leverage our unique experiences operating instruments on buoys to develop a flexible and modular design of OSIRIS so that it could be integrated with different types of buoys without changing the underlying architecture. The proposed study of OSIRIS is a first step toward enabling the proliferation of ionospheric measurements from the ocean surface. It is anticipated that the design solution developed here for ocean buoys could lead to miniaturization of OSIRIS for future CubeSat missions. The development of this new class of observing capability will be a pathfinder for future persistent ionospheric measurements from the ocean surface. This effort addresses a critical gap in our current observational capability from the ocean surface.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

We expect that the data from OSIRIS instruments when realized in its fullest will provide complementary data to the NASA GOLD and ICON missions. Future NASA missions, such as the Geospace Dynamics Constellation (GDC) mission, would also benefit from distributed arrays of OSIRIS in the Atlantic and Pacific oceans. Furthermore, the miniaturization of the imager in this project would be able to be transitioned for future NASA CubeSat missions.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Data from the OSIRIS instrument from buoys will support ionosphere-thermosphere research in academia, the DoD, and other federal agencies. Further, the versatility of OSIRIS would enable the instrument to be used to address multiple application ranging from coastal security to meteorology. For example, the proposed instrumented could be configured to provide cloud observations.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z4.05-5920
SUBTOPIC TITLE:
 Nondestructive Evaluation (NDE) Sensors, Modeling, and Analysis
PROPOSAL TITLE:
 Novel Thermosonic In-Process Nondestructive Evaluation of Additive Manufacturing Build
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
X-wave Innovations, Inc.
555 Quince Orchard Road, #510
Gaithersburg, MD 20878
(301) 200-8368

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Haidong Zhang
E-mail:
hzhang@x-waveinnovations.com
Address:
555 Quince Orchard Road, Suite 510 Gaithersburg, MD 20878 - 1464
Phone:
(301) 355-0488

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Jennifer Duan
E-mail:
jduan@x-waveinnovations.com
Address:
555 Quince Orchard, Suite 510 Gaithersburg, MD 20878 - 1464
Phone:
(301) 200-8368
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Metal additive manufacturing has become a new revolutionary for industrial manufacturing systems, providing a great potential for in-space servicing and manufacturing for NASA’s mission. However, a primary challenge in this immature process is the lack of knowledge and controlling of the microstructure formation and evolution through this method, especially for the in-process interface between layers where defects are likely to be generated. Although after-process destructive inspection may provide information about the grain’s microstructure for the additively manufactured part, the after-process characterization does not reveal critical in situ information and thus the possibility for in situ correction. Therefore, any means to measure surface and buried defects in situ efficiently with a high spatial resolution would be highly desirable. To address this critical need, X-wave Innovations, Inc. (XII) proposes to develop an innovative optical-thermal-thermosonic-infrared (OTTI) imaging technology for the nondestructive, in-process inspection of critical flaws both on the layer surface and inside the welded build. The proposed NDE technique builds on the XII-developed multi-frequency thermosonic infrared technology, which is capable of detection of defects as small as micron-size. Combined with the optical and thermal imaging techniques, OTTI reveals unprecedented information in situ on defect formation between layers and microstructure evolution on the layers, which can lead to further in situ correction and control for the structure and quality of the building part during the additive manufacturing process. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

It is estimated that the proposed system will have a substantial impact in the following NASA programs: Materials, Materials Research, Structures, and Assembly program, In-Space Propulsion Technologies Project, Advanced Telescope Technologies program, Air Vehicle Technology program, Small Spacecraft Technologies program, as well as the On-orbit Servicing, Assembly, and Manufacturing (OSAM) program, and other efforts where additive manufacturing are being engineered at NASA.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

OTTI technology significantly improves additive manufacturing in multiple ways including design, development, evaluation, analysis, and product quality control. Therefore, OTTI technology is critical for implantation of additive manufacturing into broad industries. Our customers will include US government agencies, universities, and commercial companies.

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.02-6080
SUBTOPIC TITLE:
 Technologies for Active Microwave Remote Sensing
PROPOSAL TITLE:
 Broadband Millimeter-Wave Hybrid Circulators for NASA Missions
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Micro Harmonics Corporation
20 South Roanoke Street, Suite 202
Fincastle, VA 24090
(540) 473-9983

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
David Porterfield
E-mail:
david48@mhc1.com
Address:
20 South Roanoke Street, Suite 202 Fincastle, VA 24090 - 3102
Phone:
(434) 409-4044

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Diane Kees
E-mail:
Diane@mhc1.com
Address:
20 South Roanoke Street, Suite 202 Fincastle, VA 24090 - 3102
Phone:
(540) 473-9983
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Y-junction circulators are used to direct signal flow in millimeter-wave (MMW) transmit/receive systems including radar and high speed data links. At the heart of the device is a ferrite core located at the junction of three waveguides. The magnetically biased ferrite is non-reciprocal which gives rise to the unique circulator behavior. Circulators are available with full waveguide band operation up to 40 GHz, although the isolation is generally less than 16 dB. At higher frequencies the bandwidth is severely limited by the ferrite material properties. Y-junction circulators operating between 50-90 GHz typically have bandwidths near 2 GHz and above 100 GHz the bandwidth is only 1 GHz, making them unsuitable for many systems.

What is needed is an all-new approach to the problem. We propose a novel hybrid circulator comprising an orthomode transducer (OMT) and a modified Faraday rotation isolator. These two devices can be combined to form a hybrid circulator that can operate with very high isolation over nearly full rectangular waveguide bands. Circulators with this level of performance simply do not exist in the commercial market. The hybrid circulator is thus an enabling technology, offering significantly improved performance over the current state-of-the-art. At the end of the Phase I contract, we will deliver a prototype hybrid circulator covering the 150-190 GHz band to NASA. This component will find application in NASA G-band radar systems designed for future cloud, water, and precipitation missions.

Micro Harmonics is uniquely qualified to carry out this research. We have demonstrated the accuracy of our ferrite models through previous highly successful NASA SBIR contracts. We currently produce the most advanced Faraday rotation isolators on the global market with insertion loss less than 2 dB in the WR-3.4 band 220-330 GHz. We are extending coverage to 500 GHz. With the proposed SBIR funding we have an opportunity to transform the MMW circulator technology.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Broadband, hybrid MMW circulators should find immediate use in a wide range of NASA instruments including G-Band radar for measuring microphysical properties of clouds and upper atmospheric constituents as well as airborne science systems such as NASA Cloud Radar System (CRS) high altitude aircraft and APR-3 precipitation radar. Our initial prototype will cover the band 150-190 GHz and thus meet the needs of NASA G-band (167-175 GHz) remote sensing radars designed for future cloud, water, and precipitation missions.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Broadband hybrid millimeter-wave circulators are useful in many high-frequency transmit/receive systems including high speed data links and radar. Military applications include battlefield radar, compact range radar, imaging systems, covert communications, and chemical and bio-agent detection. Commercial applications include 5G/6G backhaul radios, airport radar and aeronautic vision enhancement.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z10.04-6073
SUBTOPIC TITLE:
 Manufacturing processes enabling lower-cost, in-space electric propulsion thrusters
PROPOSAL TITLE:
 Robust Ceramics for Hall-Effect Thruster Discharge Channels
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Ceramics Manufacturing
7800 South Nogales Highway
Tucson, AZ 85756
(520) 547-0850

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Zachary Wing
E-mail:
zwing@acmtucson.com
Address:
7800 South Nogales Highway Tucson, AZ 85756 - 9645
Phone:
(520) 547-0861

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mark Angier
E-mail:
mangier@acmtucson.com
Address:
7800 South Nogales Highway Tucson, AZ 85756 - 9645
Phone:
(520) 547-0856
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Electric propulsion for space is attractive for NASA, military, and commercial missions. NASA has identified manufacturing issues that have resulted in significant costs to achieve performance repeatability and hardware reliability. Without addressing the process and materials issues, both the production of existing thrusters and the development of new thrusters will continue to face the prospect of high costs.

Current Hall effect thrusters make use of hexagonal boron nitride (BN) for the discharge channel in which plasma is generated and accelerated. Current materials have exhibited substantial lot-to-lot variability. Such material property inconsistencies have thus necessitated costly thruster design features to improve survivability margins against mechanical and thermal shock.

ACM has identified a key approach to improve the lot-to-lot consistency of BN based channel materials. ACM’s PAL process technology will produce a highly uniform microstructure after hot pressing. This will produce a high performance, repeatable BN material that is ideal for Hall effect thruster channels.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed technology will find NASA use in HERMES propulsion system, in future deep space propulsion systems, and for station keeping of near Earth research satellites.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed technology will find use in commercial satellite propulsion systems.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z7.06-5914
SUBTOPIC TITLE:
 Diagnostic tools for high enthalpy and high temperature materials testing and analysis
PROPOSAL TITLE:
 Multifunctional Laser System for 1D and 2D Imaging Diagnostic for High-Enthalpy Test Facilities
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Speckodyne Corporation
91 Robin Drive
Hamilton, NJ 08619
(609) 375-7631

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Laura Dogariu
E-mail:
laura.dogariu@speckodyne.com
Address:
91 Robin Dr Hamilton, NJ 08619 - 1158
Phone:
(609) 375-7631

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Laura Dogariu
E-mail:
laura.dogariu@speckodyne.com
Address:
91 Robin Dr Hamilton, NJ 08619 - 1158
Phone:
(609) 375-7631
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Speckodyne Corp. in collaboration with Plasma TEC, Inc. and Princeton University proposes to develop a novel, multifunctional optical diagnostic platform for kilohertz rate, non-intrusive, quantitative 1D and 2D imaging of relevant gas parameters in arc driven and other high enthalpy ground testing facilities. The platform implements and integrates state-of-the art optical diagnostic techniques that are enabled by femtosecond-based nonlinear optics: hybrid picosecond/femtosecond Coherent Anti-Stokes Raman Scattering (CARS) and Two-photon Absorption Laser induced Fluorescence (TALIF). The hybrid CARS provides single shot point and line measurements of molecular species concentrations and state populations, as well as rotational and vibrational temperatures, whereas the TALIF provides line and planar measurements of atomic oxygen, nitrogen, argon and other atomic species concentrations. Extending the TALIF to the measurement of velocity profiles will also be considered based on atomic fluorescence Femtosecond Laser Electronic Excitation Tagging (FLEET). Both FLEET and hybrid CARS were recently demonstrated in Mach 10 to 18 in nitrogen flow at AEDC Tunnel 9 in Maryland by the Plasma TEC-Speckodyne team. The proposed platform is powered by a single kilohertz-rate femtosecond laser and incorporates a high-speed imaging system. The system architectural strategy is designed to meet transportability requirements and reliable operation in the harsh environment of NASA’s large-scale ground test and evaluation facilities. The completion of the Phase I effort will demonstrate the feasibility of this concept of measuring dissociation fraction, species, nonequilibrium and temperature at kHz rate over the wide range of operational conditions characterizing high-enthalpy wind tunnel flows. The development of the system requirements and specification will support the next-phase effort focused on prototype development, implementation and testing at NASA’s ground-based facilities.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The Phase I effort will provide a demonstration of feasibility of the multifunctional optical diagnostic system that meets the requirements for operation in harsh requirements at NASA’s ground-based test facilities. Phase I will provide a blueprint for a movable system, and a prototype system capable of quantitative 1D and 2D imaging of relevant gas parameters will be developed under a Phase II effort. The system prototype will be then deployed and tested under various conditions at several NASA facilities (LaRC, ARC, GRC).

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

A robust and versatile multifunctional optical diagnostic prototype will find commercial applications in fields such as aerospace, combustion and plasma physics. Using a single laser as a source for several diagnostics make this system attractive because of a reduced size and price, and the fact that it is mobile makes it versatile for use in facilities with more than one laboratory.

Duration: 6

PROPOSAL NUMBER:
 20-1- H9.01-6134
SUBTOPIC TITLE:
 Long Range Optical Telecommunications
PROPOSAL TITLE:
 High Power (50W), 1.5um WDM Fiber Laser Transmitter with Effective FWM Mitigation
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Fibertek, Inc.
13605 Dulles Technology Drive
Herndon, VA 20171
(703) 471-7671

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Doruk Engin
E-mail:
dengin@fibertek.com
Address:
13605 Dulles Technology Drive Herndon, VA 20171 - 4603
Phone:
(703) 471-7671

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Tracy Perinis
E-mail:
tperinis@fibertek.com
Address:
13605 Dulles Technology Drive Herndon, VA 20171 - 4603
Phone:
(703) 471-7671
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

NASA’s Space Communications and Navigation (SCaN) roadmap for 2025 and beyond shows the need for optical links for Earth, lunar, inter-planetary, and relay networks requiring 10-100x higher data rates than current state-of-the-art space-based optical communications systems. Future laser communications system requirements include data rates >1 Gbps downlink from planetary bodies, and >100 Gbps low-geosynchronous earth orbit (LEO-GEO) networks. To support high-data-rate communications for long-range GEO and inter-planetary missions, a new class of laser communications transmitter is required with high average power (>20 W), high efficiency (>20%), and high peak power (>1 kW)—and capable of 16-ary and 128-ary pulse position modulation (PPM) formats. Wavelength-division multiplexed (WDM) systems must also have output power that is spectrally flat with minimal cross-talk.

Fibertek proposes to develop and demonstrate a high λ-channel count (up to 20 channels), gain-flat, high power, spaceflight prototype transmitter with an innovative Four Wave Mixing (FWM) mitigation capability or deep space optical communication (DSOC) links.  High power, multi-wavelength channel fiber amplifiers are fundamentally limited in channel count scaling to 4 channels and power scaling due to FWM non-linearities causing Pulse Energy Variation (PEV).  Our innovative approach effectively mitigates FWM resulting in compact, efficient, reliable and space-qualifiable system.  These enhancements increase the data capacity scaling by >10x over the current state of the art high power WDM transmitter enabling the next generation of high speed DSOC links.

m.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA SCaN (Space Communications and Navigation Program) roadmap to enable large science data volume returns from deep space missions. NASA exploration mission to Mars, planets and asteroid belts will benefit from much higher data rates and longer ranges than the current state of the art. NASA initiatives to support large 100G + core GEO networks. High-data rate, multi-channel laser transmitters, enable high-volume data link for science missions, hyper-spectral imaging, JPSS (Joint Polar Satellite System), Landsat, and radar/lidar missions.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

This effort supports the need for large data volume DoD and commercial GEO inter-satellite networks and high data volume downlink and LCRD (Lunar Communication Relay Demonstrator) style relay.

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.01-6160
SUBTOPIC TITLE:
 Lidar Remote Sensing Technologies
PROPOSAL TITLE:
 High-Reliability Space-Qualified LIDAR Source Packages
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Freedom Photonics, LLC
41 Aero Camino
Santa Barbara, CA 93117
(805) 967-4900

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Leif Johansson
E-mail:
leif@freedomphotonics.com
Address:
41 Aero Camino Goleta, CA 93117 - 9311
Phone:
(805) 967-4900

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Milan Mashanovitch
E-mail:
mashan@freedomphotonics.com
Address:
41 Aero Camino Santa Barbara, CA 93117 - 3104
Phone:
(805) 967-4900
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 6
Technical Abstract (Limit 2000 characters, approximately 200 words)

In this program, Freedom Photonics will develop a compact, space-qualified LIDAR seed source package at TRL 6.  The low SWaP presented by our monolithic photonic integration approach is attractive for small satellite and UAV applications, and the proposed work is necessary in order to mitigate the risk of environmental failure during the harsh conditions of launch and spaceflight.   In collaboration with NASA LaRC, the proposed packaging and reliability work will identify and implement aerospace-compatible assembly methods, components, materials, and design. 

The package assembly and design in this program will directly translate to other wavelengths and photonic architectures, and we have selected methane LIDAR as the initial target application in order to leverage the successful 1645 nm integration platforms we developed with the support of NASA GSFC.  This space qualification effort will ultimately facilitate satellite-based water vapor DIAL and remote sensing of other atmospheric gases.

The Phase I effort will culminate in a prototype LIDAR seed source hardware deliverable, assembled using materials and processes suitable for a small satellite payload.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

This program was inspired by an existing need within NASA (LaRC) for new, more precise and powerful remote sensing instrument implementations. The space qualification campaign focuses on package design and assembly, which is directly applicable to other PIC architectures at other wavelengths, so it is relevant for high-resolution LIDAR mapping of water vapor or other atmospheric gases.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

This technology will enable our compact PICs to survive launch and spaceflight. Methane LIDAR is relevant to oil and gas exploration; at other wavelengths, space-qualified LIDAR source packages can be used for terrestrial surveys by military satellites, UAVs and aircraft. The extensive risk mitigation of the space qualification may make our LIDAR sources attractive for automotive applications.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z5.04-6543
SUBTOPIC TITLE:
 Technologies for Intra-Vehicular Activity Robotics
PROPOSAL TITLE:
 Programming-Free Manipulation-in-the-Box Solution for Autonomous IVA
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Robotic Materials Inc
1860 38th street
Boulder, CO 80301
(303) 717-1436

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Nicolaus Correll
E-mail:
nikolaus@roboticmaterials.com
Address:
1860 38th street Boulder, CO 80301 - 2620
Phone:
(303) 717-1436

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Nicolaus Correll
E-mail:
nikolaus@roboticmaterials.com
Address:
1860 38th street Boulder, CO 80301 - 2620
Phone:
(303) 717-1436
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 6
Technical Abstract (Limit 2000 characters, approximately 200 words)

The goal of this project is to make a series of manipulation algorithms for bin picking, object recognition, pose estimation, and assembly as well as a STRIPS-like task planner available as a "manipulation-in-a-box" solution that can be integrated with existing robots, such as Robonaut 2, via a ROS interface. In Phase I, this integration will be demonstrated using the Gazebo simulation environment in a manufacturing environment containing a dual-arm torso, a gantry system, and multiple 3D perception sensors, and optionally, on the official Robonaut 2 simulator, pending a software usage agreement. We will demonstrate a series of sensor-based mobile manipulation tasks such as a kitting task under varying levels of sensor noise and dynamic mission conditions. Here, the manipulation-in-a-box solution leverages the robot's on-board sensors, but performs all necessary computations with an energy footprint of less than 10W. The final deliverable is a complete manipulation solution that can be configured using a browser and interface with either a simulator or real hardware via ROS. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The manipulation-in-a-box solution is directly applicable to a multitude of NASA robotic systems such as Robonaut 2 and Valkyrie. Bin picking, object manipulation, and assembly are high-value tasks that enable the robot to perform IVA activities with and without human supervision, dramatically extending maintenance and preparation task Robonaut 2 could perform on ISS or "The Gateway". 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Robotic Materials Inc. is actively marketing an autonomous, mobile manipulation solution to the manufacturing industry with an existing deployment in Denver. The proposed activities will help us to improve this product, but also pave the way fro RM Inc. to move from wheeled to humanoid robots in the future, opening up other application domains including household and elderly care. 

Duration: 6

PROPOSAL NUMBER:
 20-1- S5.06-4720
SUBTOPIC TITLE:
 Space Weather R2O/O2R Technology Development
PROPOSAL TITLE:
 Improved Satellite Robustness through Application of Erosion Resistant and High Emissivity Coatings
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Faraday Technology, Inc.
315 Huls Drive
Englewood, OH 45315
(937) 837-7749

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Rajeswaran Radhakrishnan
E-mail:
rajeswaran@faradaytechnology.com
Address:
315 Huls Drive Englewood, OH 45315 - 8983
Phone:
(937) 836-7749

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
E. Jennings Taylor
E-mail:
jenningstaylor@faradaytechnology.com
Address:
315 Huls Drive Englewood, OH 45315 - 8983
Phone:
(937) 836-7749
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

This program will address the stated need from the National Space Weather Strategy and Action plan to “enhance the Protection of National Security, Homeland Security, and Commercial Assets and Operations against the Effects of Space Weather”. Specifically, we will develop and demonstrate an ion erosion resistant passive high emissivity coating that mitigates charging and erosion effects brought on by ionizing radiation. Ionizing radiation occurs as a result of space weather events like solar flares or cosmic rays and has the potential to incur cascading spacecraft damage that could lead to loss of key services such as communications, national security, remote sensing, and environmental monitoring. In Phase I we will develop a scalable electrophoretic deposition approach to apply tunable erosion resistant and highly emissive passive coatings consisting of mixtures of low work function ceramics and hard/conductive boron doped diamond materials. Both electrophoretic deposition cell and process parameters will be optimized to obtain the desired performance. The coating development activities will be guided by an evaluation of the electron-emitting properties of the coating before and after Xenon ion sputtering, across a broad range of energies, and identify first and second crossover energies, maximum yields, and energies of maximum yields. Finally, we will estimate the feasibility of transitioning this technology to pertinent spacecraft components of interest to NASA and our Phase II commercialization partners. In Phase II, Faraday, USU, and commercial partners will apply the optimized coatings to testable components and expose them to simulated launch conditions, space weather, ionospheric charging, and ion sputtering erosion. If successful we envision these materials could then be applied to platforms used within Materials International Space Station Experiment (MISSE) for further qualification, optimization, and validation within Phase III.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

This next generation ion erosion resistant high emissivity passive coating, based on low work function materials, will enable enhance durability, effectiveness, and lifetime of spacecraft and satellite components subjected to space weather ionizing radiation events. The resulting product of this work could be applied to any spacecraft component or material that could be subjected to such harsh environmental challenges. Furthermore, it would be of interest to platforms include spacecraft skin, solar panels, circuit boards, and emitters.  

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

At the end of a successful program we envision our initial entry point will be focused on improving the resilience of solar cells due to ongoing relationships with solar cell manufacturers and the known challenges associated with space weather events occurring on these materials. Subsequent opportunities will be for other commercial satellite components that suffer from space weather effects.

Duration: 6

PROPOSAL NUMBER:
 20-1- A1.07-6115
SUBTOPIC TITLE:
 Propulsion Efficiency - Turbomachinery Technology for High Power Density Turbine-Engines
PROPOSAL TITLE:
 Lightweight Recuperator for Electrified Aircraft Propulsion
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Micro Cooling Concepts, Inc.
7522 Slater Avenue, #122
Huntington Beach, CA 92647
(714) 847-9945

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
David Underwood
E-mail:
daveunderwood@microcoolingconcepts.com
Address:
7522 Slater Avenue, #122 Huntington Beach, CA 92647 - 7738
Phone:
(714) 227-9025

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
David Underwood
E-mail:
daveunderwood@microcoolingconcepts.com
Address:
7522 Slater Avenue, #122 Huntington Beach, CA 92647 - 7738
Phone:
(714) 227-9025
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Electrified Aircraft Propulsion (EAP) is a growing NASA technology effort that could enable new configurations of aircraft. With the potential to transform the transportation and services markets, vehicle classes of interest include single-aisle, thin/short haul, and urban air mobility. These vehicle concepts rely on hybrid electric systems to provide propulsive power through the use of a turbo-generator combined with electrical energy storage. For turbo-generators/range-extenders utilized in regional EAP concepts, small lightweight turboshaft engines are an excellent choice due to their maturity and availability. However, at small power scales, gas turbines are less efficient. This can be addressed by using a recuperator to inject waste heat from the turbine back into the thermodynamic cycle upstream of the combustor. Micro Cooling Concepts (MC2) has developed technologies for fabricating extremely compact metallic heat exchangers with high heat transfer while reducing size by 3-5X and weight by 2-3X, using the printed circuit heat exchanger (PCHX) approach.Using additive manufacturing to create heat exchangers with finer scale and higher aspect ratio features can magnify the advantages of MC2’s existing technology, resulting in affordable recuperators with minimal weight, volume, and pressure losses. Analysis shows that the PCHX approach gives ~50% weight reduction, while the 3D Printed/Hybrid recuperators provide an additional 20% weight reduction. These weight reductions translate directly into shorter fuel payback times and opportunities to increase payload or range. The program will begin with requirements definition and design studies to size the heat exchanger and assess flow distribution. 3D printing studies will assess manufacturability of the concept, followed by fabrication and testing of proof pressure test specimens, representative of a full-scale recuperator design. The program will conclude with a design update to prepare for the Phase II effort.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Technology applicable to any NASA program where heat exchangers are required and weight has a significant impact on system performance. Examples include:

 

  • Ultra-Efficient Commercial Vehicles
  • Transition to Low-Carbon Propulsion
  • Advanced Air Transportation Technology (AATT) Project
  • Revolutionary Vertical Lift Technology (RVLT)
  • Convergent Aeronautics Solutions (CAS) Project
  • ASCENDS (Active Sensing of CO2 Emission Nights, Days, Seasons)
  • DRM 5/6/7/8/9 (Asteroid Redirect, Crewed to Asteroid/Moon/Mars)
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Lightweight compact heat exchangers have uses across wide range of applications. Impact cannot be overstated as applicability to military and commercial sectors is vast.

 

  • Energy / Transportation / Space
Duration: 6

PROPOSAL NUMBER:
 20-1- A1.02-5961
SUBTOPIC TITLE:
 Quiet Performance - Aircraft Propulsion Noise
PROPOSAL TITLE:
 Comprehensive Acoustic Analysis for Urban Air Mobility Vehicles
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing, NJ 08618
(609) 538-0444

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Daniel Wachspress
E-mail:
dan@continuum-dynamics.com
Address:
34 Lexington Avenue Ewing, NJ 08618 - 2302
Phone:
(609) 538-0444

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Barbara Agans
E-mail:
barbara@continuum-dynamics.com
Address:
34 Lexington Avenue Ewing, NJ 08618 - 2302
Phone:
(609) 538-0444
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

A major innovative thrust in urban air mobility (UAM) is underway that could potentially transform how we travel by providing on-demand, affordable, quiet, and fast passenger-carrying operations in metropolitan areas using novel air vehicles, most employing some form of Distributed Electric Propulsion (DEP).  The need to support the rapid maturation of technology for UAM is a key motivation for the current NASA UAM Grand Challenge.  As noted by NASA, “the Grand Challenge aims to improve UAM safety and accelerate scalability through integrated demonstrations by hosting a series of UAM ecosystem-wide challenges beginning in 2020” addressing a wide range of technical impediments to the growth of UAM, including, notably, the need to characterize vehicle noise levels.  The proposed effort will both build on recent major advances in noise modeling at CDI and, in the long term, support of the acoustics analysis goals of the Grand Challenge by enhancing state-of-the-art rotary-wing aeromechanics and acoustics analysis with key additional modeling capabilities needed for comprehensive prediction of DEP aircraft noise, focusing initially on the special problems associated with the prediction of noise from multiple, time-varying RPM systems.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The comprehensive acoustic analysis proposed would enable accurate prediction of acoustics of UAM aircraft in computation times commensurate with daily design work, and would directly support NASA’s ARMD Strategic Thrust #4 (Safe, Quiet, and Affordable Vertical Lift Air Vehicles) in their Technology Roadmap.  The developed analysis would be of immediate use to NASA engineers and UAM developers in evaluating and designing low-noise DEP configurations and identifying methods to reduce noise of UAM vehicles.   

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

CDI collaborates with eVTOL UAM vehicle developers who have an immediate need for the proposed analysis to predict aircraft noise during conceptual design.  The analysis will also be of great value to the DoD and major rotorcraft manufacturers in analyzing acoustic characteristics of future vertical lift concepts like those under development for the U.S. Army Future Vertical Lift (FVL) program.

Duration: 6

PROPOSAL NUMBER:
 20-1- H9.03-5963
SUBTOPIC TITLE:
 Flight Dynamics and Navigation Technology
PROPOSAL TITLE:
 Maneuver Characteristics of Autonomous Non-Cooperative Spacecraft
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Omitron, Inc.
7051 Muirkirk Meadows Drive, Suite A
Beltsville, MD 20705
(301) 474-1700

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Karen Thomson
E-mail:
Karen.Thomson@omitron.com
Address:
7051 Muirkirk Meadows Drive, Suite A Beltsville, MD 20705 - 6342
Phone:
(301) 474-1700

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Bryan Larsen
E-mail:
bryan.larsen@omitron.com
Address:
7051 Muirkirk Meadows Drive, Suite A Beltsville, MD 20705 - 6342
Phone:
(301) 474-1700
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

SpaceX has launched several hundred of a planned constellation of several thousand Starlink satellites into nominal 550 km altitude circular orbits.  The Starlink spacecraft reportedly operate largely autonomously, to include maneuvering to avoid collisions with other spacecraft and debris.  Collision avoidance maneuvers are not published and may not be known even to Starlink until after they occur.  Starlink operational parameters and concept of operations (ConOps) are only partly known to 18 SPCS and CARA.  The Starlink constellation is therefore comprised of autonomous, non-cooperative spacecraft.  The native 18 SPCS OD and O/O ephemeris are unreliable means of predicting future Starlink spacecraft positions necessary for Conjunction Assessment (CA).  More concerning is that the O/O ephemeris is used for CA screening and the results are published to Starlink for use in determining avoidance maneuvers.  CARA must therefore rely entirely on Starlink spacecraft to maneuver to avoid potential collisions with CARA-protected payloads while having no knowledge of the characteristics of such maneuvers or the underlying methodology used in their planning and execution.   Research is therefore proposed to characterize the maneuver behavior of autonomous, non-cooperative spacecraft in response to predicted CA data by analyzing historical data using machine learning and traditional analysis techniques.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Capability to predict either specific maneuvers or a range of expected maneuvers – a maneuver envelope – that can be analyzed for post-maneuver risk to CARA-protected missions for both station keeping and avoidance maneuver operations.  If successful, the approach can be applied to other non-cooperative spacecraft whether or not operating autonomously and to future mega-constellations similar to Starlink that use autonomous operations.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Government and commercial entities CA risk analysis and Space Traffic Management practitioners DoD, DoC, SpaceNav, AGI, and commercial sensor data providers.  Maneuver reconstruction success will result in improved 18 SPCS OD performance by automating detection/solution of autonomous low-thrust maneuvers.  Informs future policy development for CA practice by the commercial space industry.

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.01-6553
SUBTOPIC TITLE:
 Lidar Remote Sensing Technologies
PROPOSAL TITLE:
 Thirty Millijoule Single Frequency 2 Micron Fiber Lasers for Coherent Wind Lidar
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
AdValue Photonics, Inc.
2700 East Bilby Road
AZ, AZ 85706
(520) 790-5468

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Shibin Jiang
E-mail:
sjiang@advaluephotonics.com
Address:
3440 East Britannia Drive, Suite 190 Tucson, AZ 85706 - 5285
Phone:
(520) 790-5468

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Shibin Jiang
E-mail:
sjiang@advaluephotonics.com
Address:
3440 East Britannia Drive, Suite 190 Tucson, AZ 85706 - 5285
Phone:
(520) 790-5468
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

The NASA’s Doppler Aerosol WiNd (DAWN) lidar system needs a pulsed single frequency laser operating near 2 micron lase wavelength. We propose a new type of Tm-doped fiber for this application. The overall objective of this proposal is to demonstrate and build a single frequency near 2 micron fiber laser with pulse energy of greater than 30mJ. Tm-doped gain fiber with excellent radiation resistance against high energy radiation will be used. This proposed laser will be all-fiber PM laser with a beam quality of 1.2. In Phase II we will demonstrate and deliver a packaged 2 micron single frequency fiber laser with 30mJ pulse energy to NASA.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA needs single frequency high pulse energy 2 micron fiber laser for wind Lidar applications. Such a fiber laser is of great interest because of the potential possibility of combining high efficiency, high output power, and retina safety together. This technical approach can also be used for CO2 measurement by using Ho-doped fiber. 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

There are a number of potential non-NASA commercial applications for 1.94 micron fiber laser. This eye-safe laser source can be used to build commercial lidar for ranging and surface topography applications, be used as the light source for fiber optical sensing, fast scanning biomedical imaging, and scientific research.

Duration: 6

PROPOSAL NUMBER:
 20-1- S4.04-5367
SUBTOPIC TITLE:
 Extreme Environments Technology
PROPOSAL TITLE:
 Radiation-Hardened Wide-Temperature Analog/Mixed-SignalLibrary in a 22nm FDSOI CMOS Process
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Alphacore, Inc.
304 South Rockford Drive
Tempe, AZ 85281
(480) 494-5618

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Marek Turowski
E-mail:
engineering@alphacoreinc.com
Address:
398 South Mill Avenue, Suite 304 Tempe, AZ 85281 - 2480
Phone:
(480) 494-5618

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Andrew Levy
E-mail:
andrew.levy@alphacoreinc.com
Address:
398 South Mill Avenue, Suite 304 Tempe, AZ 85281 - 2480
Phone:
(503) 320-5466
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Wide temperature and radiation hardened CMOS based monolithic chips are sought by NASA for both onboard scientific instruments (such as radiometers and spectrometers) and for high performance computing (HPC). Analog blocks have long been a critical need for NASA’s missions, such as Moon missions and Europa. Alphacore, Inc. will design and characterize wide-temperature (-200 °C to +200 °C) rad-hard (TID calibrated, SEL immune, SET tolerant) CMOS analog library in the GlobalFoundries (GF) 22nm FDSOI CMOS process, which will help realize next generation extreme environment operable ASICs for future NASA’s missions. 

 

Alphacore’s analog library includes key analog blocks that most scientific instruments and sensors would need for all future missions. These blocks include 1) programmable resolution and sampling rate Analog to Digital Converter (ADC) 2) Digital to Analog Converter (DAC) 3) Low-Dropout (LDO) regulator and 4) Comparator.  These blocks will be designed in 22nm FDSOI process that will have TID calibration with SEL immunity and SET tolerance and suitable for applications of wide temperatures like atmospheric and surface explorations of Titan (-180° C), Europa (-220° C), Ganymede (-200°C), Mars (-120°C to +20°C), the Moon (-180°C), asteroids, comets and other small bodies.  

 

What Alphacore is proposing is a unique solution to critical need that has not previously been addressed. Alphacore has been closely collaborating with multiple teams that researched state-of-the-art circuits including readout systems, sensors and other mixed signal circuits for analog data capture, signal processing, command and control. Since Alphacore has been actively involved in radiometer system designing community for over three years, we have a deep understanding of the scientific payloads and rad-hard, cold temperature mixed signal circuits community’s needs and of related design challenges. 

 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Alphacore’s proposed analog library includes blocks designed in 22nm FDSOI process, suitable to function under high-radiation and wide temperatures of planets, asteroids and comets in deep space. Future NASA missions that could benefit from components designed using Alphacore’s rad-hard library include Europa Clipper, Europa Lander, and Venus Emissivity, Radio Science, InSAR, Topography, and Spectroscopy (VERITAS), and the Titan Saturn System Mission, along with the Moon-to-Mars program and the Origins Space Telescope. 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

By supporting the development of advanced radiation-hardened components for space, Alphacore’s innovation can help enhance current technological capabilities and also achieve new and innovative scientific measurements for space discoveries and exploration; scientists will be able to gain a better knowledge of the universe and physics. 

 

Duration: 6

PROPOSAL NUMBER:
 20-1- Z2.02-5369
SUBTOPIC TITLE:
 High Performance Space Computing Technology
PROPOSAL TITLE:
 Radiation Tolerant Standard Cell Library in a 22nm FDSOI CMOS Process
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Alphacore, Inc.
304 South Rockford Drive
Tempe, AZ 85281
(480) 494-5618

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Marek Turowski
E-mail:
engineering@alphacoreinc.com
Address:
398 South Mill Avenue, Suite 304 Tempe, AZ 85281 - 2480
Phone:
(480) 494-5618

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Dave Johnson
E-mail:
dave.johnson@alphacoreinc.com
Address:
304 S Rockford Dr Tempe, AZ 85281 - 0000
Phone:
(480) 494-5618
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

NASA is seeking radiation tolerant standard cell libraries for processes below 28nm that are suitable for NASA missions in the natural space environment. As a response, Alphacore proposes a complete library of radiation-hard standard cells implemented in the GlobalFoundries 22nm fully depleted silicon on insulator (FDSOI) CMOS fabrication process (GF 22FDX). 

With CMOS downscaling, the soft error rate (SER) due to radiation-induced charge generation and collection in sensitive nodes of integrated circuits  improves at the device level. However, as more memories and latches are integrated per chip, the chip-level SER increases with each new technology node. Thus, single-event effects (SEE) are a crucial concern in advanced nodes for high-reliability applications in space, atmospheric, and terrestrial radiation environments. SOI technologies have shown significant improvements in SEE resiliency due to reduction in charge deposition in sensitive volumes, immunity to single-event latch-up (SEL), and suppression of charge sharing mechanisms. In particular, Ultra-Thin Body and BOX technologies, such as 28nm and 22nm FDSOI, show excellent resiliency to SEEs and very low SER. 

The Phase I program will strongly leverage Alphacore’s existing 22FDX radiation effect characterization, radiation hardening by design (RHBD), and overall mixed-signal IP development work. With its extensive experience in this area, Alphacore will have a complete radiation tolerant library designed by the end of the Phase I program.  In Phase II, a complete radiation tolerant standard cell library will be fabricated and tested. The elements will be tested for functionality, circuit performance and radiation hardness, including both SEE and total ionizing dose (TID). Alphacore will also schedule another major tapeout within the Phase II program and containing optimized cells, ready to be used by NASA and other customers in their applications needing both excellent performance and radiation hardness. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA programs that will benefit from Alphacore’s rad-hard standard cell library include target applications for the High-Performance Spaceflight Chiplet (HSPC) ecosystem within Human Exploration and Operations Mission Directorate (HEOMD) and Science Mission Directorate (SMD), and future missions such as the Mars Fetch Rover, the WFIRST, the Lunar Gateway and SPLICE. The rad-hard library will also help the design of a wide range of space electronics outside of space-computing applications.  

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

By supporting the development of advanced radiation-hardened components for space, Alphacore’s innovation can help enhance current technological capabilities and also achieve new and innovative scientific measurements for space discoveries and exploration; scientists will be able to gain a better knowledge of the universe and physics. 

Duration: 6

PROPOSAL NUMBER:
 20-1- H5.01-5432
SUBTOPIC TITLE:
 Lunar Surface Solar Array Structures
PROPOSAL TITLE:
 Origami-Based Extendable Lunar Innovative Solar Column (OBELISC)
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
LoadPath
2309 Renard Place Southeast, Suite 101
Albuquerque, NM 87108
(866) 411-3131

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Nathan Pehrson
E-mail:
npehrson@loadpath.com
Address:
2309 Renard Place Southeast, Suite 101 Albuquerque, NM 87108 - 1862
Phone:
(801) 300-8161

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Gregory Sanford
E-mail:
gsanford@loadpath.com
Address:
2309 Renard Place SE, Suite 101 Albuquerque, NM 87108 - 1862
Phone:
(866) 411-3131
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

 For upcoming Lunar-surface missions that require autonomous vertically deploying, efficient, robust, and retractable solar arrays near the south pole, Origami-Based Extendable Lunar Innovative Solar Column (OBELISC) is a simple packaging, deployment, and scalable architecture for a non-rotating column solar array. Featuring single-axis vertical deployment and retraction, OBELISC is a low-maintenance, robust design leading to long life and multiple retractions for relocation or service. Unlike a rotating flat array, OBELISC’s design boasts a 360-degree view with no need for a vertical axis gimble. The enclosed internal mechanisms are protected from lunar dust by the blanket array and reduction in complexity (and therefore the number of failure points) increases OBELISC’s service life and reliability.

The system consists mainly of the folding blanket array and the support structure. The architecture uses an identical trapezoidal facet repeated throughout the entire array, with each side of the column folding compactly in a z-folded manner. The trapezoidal facets are populated with PV cells and the triangular facets are left unpopulated but are retained for two purposes: control the folding and unfolding of the PV panels and act as the first line of defense against dust for the enclosed mechanisms.

The OBELISC architecture is tailorable in stowed inner and outer diameters, number of sides, and number of bays. The outer diameter variability allows for convenient integration onto common lunar lander designs and within launch fairings. The inner diameter variability allows for the central support structure to be housed within the central volume. The variability of the number of sides allows for optimal design of panels versus the performance of the solar array. The variability in the number of bays increases or decreases the deployed height of the column, allowing for a tractable way to tailor the deployed area without changing the rest of the geometry.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

 OBELISC will benefit NASA initial manned and unmanned missions to the lunar surface.  These missions could use large photovoltaic solar arrays to generate power for habitats, ISRU, science investigations, and battery charging. The proposed technology could also impact a broad array of NASA missions, such as NASA’s needs for large deployable and retractable solar arrays for solar electric propulsion and hybrid propulsion schemes or for powering lunar and planetary tug spacecraft.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

OBELISC will benefit the DoD, prime contractors, and commercial spacecraft providers that are interested in large solar arrays. Specific examples include providers that endorse OBELISC development (Astrobotic and Firefly), and others such as Air Force, Army, SpaceX, and Northrup Grumman. OBELISC has Earth terrestrial applications for military, industrial operations, and temporary dwellings.

Duration: 6

PROPOSAL NUMBER:
 20-1- A1.08-4967
SUBTOPIC TITLE:
 Aeronautics Ground Test and Measurement Technologies
PROPOSAL TITLE:
 Conformal Nanomembrane based Sensor Skins for Cryogenic Shear Measurements
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Nanosonic, Inc.
158 Wheatland Drive
Pembroke, VA 24136
(540) 626-6266

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Hang Ruan
E-mail:
hruan@nanosonic.com
Address:
158 Wheatland Drive Pembroke, VA 24136 - 3645
Phone:
(540) 626-6266

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Melissa Campbell
E-mail:
mcampbell@nanosonic.com
Address:
158 Wheatland Drive Pembroke, VA 24136 - 3645
Phone:
(540) 626-6266
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

This NASA Phase I SBIR program would develop conformal nanomembrane based “sensor skins” capable of global shear stress characterization on wind tunnel models as well as operational aerospace vehicles at both room temperature and cryogenic conditions. The team will transition the conformal nanomembrane based shear stress sensors from their current concept to prototype stage products of use to NASA’s ground test facilities. The team will develop an improved mechanical and electrical model of semiconductor nanomembrane based sensor performance that will allow quantitative optimization of material properties and suggest optimal methods for sensor attachment and use for shear measurement applications. The team will perform synthesis of sensor skin materials with optimized transduction, hysteresis and environmental properties, specifically for high Reynold’s number flow and also varying temperature use at both room temperature and cryogenic conditions. A complete analysis of sensor cross-sensitivities and noise sources will be performed to allow optimization of signal-to-noise ratio and practical sensor sensitivity. Support electronics will be developed to acquire, multiplex, store and process raw sensor array data.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The accurate measurement of shear stress using the proposed global shear sensing technology in complex flows is needed for NASA ground test facilities, as current computational methods are insufficient. An appreciation of the instrumentation issues obtained by working with NASA centers would allow improvements in sensor materials, electronics and packaging, and potentially allow the transition of related products to operational vehicles.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Primary customers would be university, government laboratory and industry researchers. Use of developed global shear sensor technology first by NASA, and then by the broader research community, as well as the developers and users of aerospace, hydrospace, land vehicle, civil structure and biomedical flow systems, is envisioned.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z1.03-5485
SUBTOPIC TITLE:
 Kilowatt-Class Energy Conversion for Small Fission Reactors
PROPOSAL TITLE:
 ATEG Kilopower
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Howe Industries, LLC
1435 East University Drive Street C-108
Tempe, AZ 85281
(480) 967-5660

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Troy Howe
E-mail:
troy@howeindustries.net
Address:
140 East Rio Salado Parkway, #902 Tempe, AZ 85281 - 5499
Phone:
(480) 250-6820

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Troy Howe
E-mail:
troy@howeindustries.net
Address:
140 East Rio Salado Parkway, #902 Tempe, AZ 85281 - 5499
Phone:
(480) 250-6820
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

We propose to investigate a new approach to achieving high performance thermoelectric generators (TEGs) used in nuclear power environments that preliminary calculations suggest may result in a >20% conversion efficiency. This innovation employs the existing reactor neutron radiation coupled with boron based thermoelectric materials to significantly enhance their performance through effects that radiation is known to have on electrical conductivity of solids. The boron-10 material in a neutron field will react to create alpha particles and ionize the feet of the TEG to greatly improve material properties, resulting in an Advanced Thermoelectric Generator, or ATEG.
The major aspect of this innovation revolves around the tendency for ionizing radiation to excite the electrons in a material as it passes through. In doing so, the electrical conductivity of the material increases due to Radiation Induced Conductivity (RIC). However, it is known that the thermal and Seebeck properties of the material remain relatively unchanged. The figure of merit (ZT) for TEGs depends heavily on the electrical and thermal conductivity of the material, as well as the Seebeck coefficient. All three of these factors have been shown to improve when exposed to ionizing radiation. Based on effects seen from previous irradiation tests, the ZT of an ATEG can increase to the point where conversion efficiency can reach over 20%.
Previous work performed by Howe Industries has demonstrated the electrical conductivity change in boron nitride samples during tests at KSU. As boron based TEGs currently exist, adapting these for use with the Kilopower reactor will be the main focus of this project. Doing so will allow for an improved conversion efficiency, reliable power production, and minimal changes to the current designs. This project has the potential to not only increase the performance of the Kilopower reactor, but also decrease overall mass and design complications. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The ATEG system can be used for fission surface power with reactors as well as for high efficiency conversion with radioisotopes. Substituting the boron material with americium dopant allows for power generation uncoupled from a neutron source. Having a 20% efficient TEG would decrease the overall amount of radioisotope fuel required for deep space missions and enable larger missions or more missions per year to take place.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The ATEG system can be adapted for use on Earth for small modular reactors, full scale nuclear power plants, and waste head reclamation. Current estimates suggest that power can be generated in an ATEG SMR for $0.02/kWh and waste heat units can produce power at $0.003/kWh. Studies have found future market predictions for SMR and thermoelectrics to be $4.5B and $741M, respectively.

Duration: 6

PROPOSAL NUMBER:
 20-1- S3.01-5487
SUBTOPIC TITLE:
 Power Generation and Conversion
PROPOSAL TITLE:
 Textured Solar Array
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
MicroLink Devices, Inc.
6457 Howard Street
Niles, IL 60714
(847) 588-3001

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Christopher Youtsey
E-mail:
cyoutsey@mldevices.com
Address:
6457 Howard Street Niles, IL 60714 - 3301
Phone:
(847) 549-8590

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Noren Pan
E-mail:
npan@mldevices.com
Address:
6457 Howard Street Niles, IL 60714 - 3301
Phone:
(847) 588-3001
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

This Phase I program will demonstrate an innovative, module-level encapsulation technology that will lower the cost by at least 50% and enhance the performance of space-grade solar arrays. Conventional solar cells for space use specialized coverglass that provides essential environmental protection from high-energy particle and ultraviolet solar radiation but is expensive to apply and has high fragility. Next-generation coverglass replacement materials have been explored by several groups over the past decade. Pseudomorphic glass (PMG) uses glass microbeads embeded in a silicone matrix that can be formed into sheets or sprayed on interconnected modules. Pure silicone sheets using space-grade DC 93-500 have also been investigated for module-level protection. Both approaches have the additional benefit of high flexibility that is synergistic with thin-film, inverted metamorphic multi-junction (IMM) solar cells manufactured by MicroLink Devices, enabling a pathway to truly flexible solar modules.

The central innovation in this proposal is to introduce a novel, prismatic texturing method that will improve the performance and manufacturability of silicone-based encapsulations including PMG. Texturing of glass encapsulants has previously been explored for enhancing high-angle light capture for terrestrial solar arrays, but prismatic structuring of space coverglass has not been widely investigated. Polymer materials are much more readily formed into prismatic shapes, which presents a new opportunity to introduce this important technique. In this Phase I program MicroLink will demonstrate that prismatic structures not only increase the high-angle collection efficiency of space solar cells by up to 30%, but also reduce the operating temperature by as much as 3 degrees. Equally important, the surface texturing is expected to substantially simplify the design and robustness of essential UV protective coating layers deposited over the encapsulation.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)
  • Spacecraft and Planetary Missions – The proposed textured modules may provide an enabling technology for large-scale SEP (solar electric propulsion) spacecraft and enable high specific power solar arrays for a variety of NASA science missions.
  • Satellites – The IMM solar modules are low mass, flexible, and power dense and as such they will be beneficial for large-scale deployment of constellation satellites and cubesats.
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)
  • Unmanned Aerial Vehicles (UAVs) – High-altitude long-endurance (HALE) solar UAVs such as the Airbus Zephyr, which have variable sun incident angles depending on time of day/year and latitude.
  • Commercial Satellites – Flexible “roll-out” arrays, LEO constellation satellites that require low cost and use body-mounted solar panels. Textured sheets can be applied to all solar cell technologies.
Duration: 6

PROPOSAL NUMBER:
 20-1- Z1.03-5493
SUBTOPIC TITLE:
 Kilowatt-Class Energy Conversion for Small Fission Reactors
PROPOSAL TITLE:
 A High Temperature Heat Rejection System for Fission Power Generation
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
ThermAvant Technologies, LLC
2508 Paris Road
Columbia, MO 65202
(573) 397-6912

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ben Alexander
E-mail:
ben.alexander@thermavant.com
Address:
1000 Pannell Street, Suite A Columbia, MO 65201 - 4786
Phone:
(573) 722-2064

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Joseph Boswell
E-mail:
joe.boswell@thermavant.com
Address:
1000 Pannell Street, Suite A Columbia, MO 65201
Phone:
(573) 397-6912
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

According to the NASA SBIR 2020 program solicitation, kilowatt-class fission power generation is an enabling technology for lunar and Mars surface missions that require day and night power for long-duration surface operations, and may be the only viable power option to achieve a sustained human presence.  In response to NASA SBIR FY 2020 topic Z1.03, Thermal Management, ThermAvant Technologies, LLC (ThermAvant) proposes to develop a high temperature, large format, high capacity Oscillating Heat Pipe (OHP) embedded radiator panel to significantly improve the size, weight and power density of future kilowatt class Fission Power Systems (FPS).  This proposal aims to develop thin profile radiator panels, e.g. greater than 1m2 scale x 2-3mm thick, used to reject heat from the waste heat (cold) side of the reactor system.  During the six-month Phase I effort, the team proposes to design and empirically demonstrate high temperature prototype radiator panels.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA is considering the use of kilowatt class Fission Power Systems for surface missions to the moon and Mars. This directly aligns with the Space Technology Mission Directorate roadmap for space power and energy storage. Prior work in fission power systems had focused on a 1kWe ground demonstration, however, NASA desires to scale-up the system and components for a flight demo mission to the lunar surface, so component technologies that support a 10kWe-class fission power system are sought after to address many remaining technical challenges.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Large-format, high capacity radiators will have applications in terrestrial vehicles with electrical loads, and in large industrial vehicles where he proposed passive solution may be able replace actively pumped single-phase radiators with air cooled systems. These panels may be a viable solution for acquiring heat and rejecting to the heat sink (air, space, water, etc.).

Duration: 6

PROPOSAL NUMBER:
 20-1- H12.05-5582
SUBTOPIC TITLE:
 Autonomous Medical Operations
PROPOSAL TITLE:
 Autonomous Guidance for Medical Procedures
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Retrocausal, Inc.
17634 NorthEast Union Hill Road, Suite 301
Redmond, WA 98052
(669) 220-8352

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Muhammad Zeeshan Zia
E-mail:
zeeshan@retrocausal.ai
Address:
17634 NE Union Hill Rd, Suite 301 Redmond, WA 98052 - 6096
Phone:
(669) 220-8352

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Muhammad Zeeshan Zia
E-mail:
zeeshan@retrocausal.ai
Address:
17634 NE Union Hill Rd, Suite 301 Redmond, WA 98052 - 6096
Phone:
(669) 220-8352
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Problem: Mars missions will not have real-time communications with Mission Control Center (MCC), and correspondingly limited access to supervision for complex medical scenarios that lie outside the skill set of crew members. Thus we need solutions that can provide just-in-time training, monitoring, and autonomous guidance of medical procedures, to make the crew independent of MCC.

Solution: We propose a system for automatically building computational models of a complex physical task, such as a medical procedure performed by humans, given only a handful of recorded expert demonstrations of the task. Once such a model is built, our system can finely analyze the same task being performed in live video, to provide measurements and analytics, improve efficiency, guide a crew member through the task, or provide just-in-time training.

We combine recent advances in machine learning and computer vision, including our own prior work, in human pose estimation, 3D object estimation, action classification, and long-term causal reasoning to build novel systems that can understand goal-driven multi-step activities in live video feed.

Existing commercial solutions: Some AI platforms offer capabilities to estimate human skeletal poses, locate objects, as well as classify simple actions in video. 

However in order to understand a certain multi-step activity (e.g. a medical procedure), a solution provider still needs a team of computer vision or IoT engineers, who write customized computer code to represent that specific activity, relating human pose changes with object movements over time, i.e. building this temporal causation structure on top of the capabilities provided by the existing AI platforms. 

In contrast, our solution is able to learn complex activities that combine human-object and human-human interaction over time merely from example demonstrations of the activity. Our system does not require customization at the level of new programming to model a new activity and scenario.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Mars missions face the challenge of significant communication delays with Mission Control, while complexity of operations keeps increasing. Thus, just-in-time training and autonomous guidance and monitoring solutions are valuable for medical operations and beyond. Our solution packages an "extra pair of trained eyes" (in the form of cameras and artificial intelligence software) to assist the crew, and we predict the solution has the potential on some missions to reduce crew headcount by 1 or more, which will mean enormous savings for NASA.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Medical learners need attending physicians or expert nurses to provide them with feedback when learning a procedure such as Lumbar Puncture on a medical simulator. Unfortunately, expert time in healthcare is incredibly valuable and also experts are not geographically scalable.

Our solution replaces the need for expert feedback at medical simulation centers saving them millions of dollars each year.

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.01-5597
SUBTOPIC TITLE:
 Lidar Remote Sensing Technologies
PROPOSAL TITLE:
 Compact Power Amplifier for Hybrid Fiber/Bulk Wind Lidar Transmitters
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Beyond Photonics, LLC
6205 Lookout Road, Suite B
Boulder, CO 80301
(303) 475-2088

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Sammy Henderson
E-mail:
sammy@beyondphotonics.com
Address:
6205 Lookout Road, Suite B Boulder, CO 80301 - 7216
Phone:
(303) 396-8536

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Charley Hale
E-mail:
charley@beyondphotonics.com
Address:
6205 Lookout Road, Suite B Boulder, CO 80301 - 7216
Phone:
(303) 475-2088
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

There is strong motivation to significantly reduce the complexity and size and to further improve the electrical-to-optical efficiency of eyesafe coherent lidar systems.  Recent advances in fiber lasers and associated components allow for compact and rugged eyesafe transmitters, but the high-spectral-purity single frequency, and high beam quality output energy needed for efficient coherent lidar systems is limited to < 1 mJ in practical all-fiber implementations.   This pulse energy is sufficient for many short-range or high-backscatter measurement applications, but to extend the measurement capability higher pulse energy is needed.  This is due to a fundamental characteristic of coherent (heterodyne) detection in the weak signal regime, where the measurement sensitivity is proportional to the product of the pulse energy and the square root of the pulse repetition frequency (PRF).  Stressing weak signal examples include measuring atmospheric winds from space platforms or measuring in the very low backscatter mid and upper troposphere from ground or airborne platforms.  To utilize the positive attributes of a fiber-based transmitter, we propose to develop a very compact integrated  bulk-crystal-based amplifier and lidar transmit/receive module that will boost the fiber transmitter output pulse energies to as much as 40 mJ per pulse at 400 Hz PRF and provide for efficient collection of the return signals.  Our initial focus will be on 2 micron wavelength devices, but the basic architecture can be applied to other wavelength as well.  Operationally flexible, highly ruggedized compact packaging with path-to-space will be emphasized.  These innovations will apply directly to current NASA missions and instruments (Space-based Winds, Airborne and Ground Based Wind lidar, IPDA, LAS) and accelerate commercial development and availability of practical ground-based and airborne systems at Beyond Photonics and elsewhere.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Potential NASA applications of the proposed hybrid fiber/bulk power amplifier/lidar transceiver technology include on-going and future measurement of global winds from space; ground-based and airborne coherent lidar programs; eye-safe remote laser spectroscopy applications for measurement of atmospheric constituents like CO2, water vapor, and methane; tracking of fast-moving space debris and asteroid hazards; spacecraft docking applications; and other shortwave-IR wavelength instrument developments in the 1.5-to-2.0 micron wavelength region.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Non-NASA uses of hybrid fiber/bulk amplifier transmitters include DoD hard target and space debris tracking/imaging problems and research/industrial applications requiring very compact efficient front-end transmitter lasers and bulk amplifiers at SWIR wavelengths. Product development is planned for compact, high-performance remote-sensing products for winds and other remote sensing applications.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z10.04-5651
SUBTOPIC TITLE:
 Manufacturing processes enabling lower-cost, in-space electric propulsion thrusters
PROPOSAL TITLE:
 Castable Inorganic Composite Potting Material for High-Temperature Electromagnets
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
HiFunda, LLC
421 Wakara Way, Suite 210
Salt Lake City, UT 84108
(801) 662-0709

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Jim Steppan
E-mail:
jsteppan@hifundallc.com
Address:
421 Wakara Way Suite 210 Salt Lake City, UT 84108 - 3546
Phone:
(801) 750-4928

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Balakrishnan Nair
E-mail:
bnair@hifundallc.com
Address:
421 Wakara Way Suite 210 Salt Lake City, UT 84108 - 3546
Phone:
(801) 897-1221
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

HiFunda’s new low-cost, castable inorganic composite potting material (CICPM) and process proposal is in response to NASA’s request for proposals that address improved materials or fabrication processes to reduce the total life cycle cost of electric propulsion thrusters.  NASA has specifically encouraged prospective proposers in fields outside of electric propulsion, like HiFunda, to apply if they have experiences with materials and processes that may be suitable for this application.  Insulation and potting degradation during thruster operations can lead to early thruster failures that have occurred with existing processes for manufacturing and potting magnetic wire. HiFunda is proposing a new geopolymer composite potting material and casting process that will extend the temperature limits of conventional polymeric and/or ceramic potting materials thereby minimizing or eliminating instances of potting and insulation failures. High-temperature electromagnet coils are potted with a ceramic material that is intended to fill the gaps between the windings and to be free of voids. Unfortunately, in practice, the ceramic potting compound develops cracks due to the large startup thermal gradients and the large difference in coefficient of thermal expansion (CTE) of the constituent materials.  The proposed technology will mitigate this issue by adding reinforcing fibers to the potting compound and more closely matching the effective CTE of the geopolymer matrix. In Phase I, HiFunda will develop and demonstrate robustness and suitability of a CICPM in a potting test vehicle (PTV) and a subscale proof-of-concept high-temperature electromagnet (POC-HTEM) simulant. The proposed technology will be further refined and demonstrated on a high-temperature electromagnet design of interest to NASA and/or aerospace contractors in Phase II.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed new low-cost castable inorganic composite potting material (CICPM) and process will be used by NASA for electromagnets in electric propulsion systems on spacecraft.  Benefits to NASA include improved reliability and longer lifetimes of high-temperature electromagnets and potential cost reduction of potting materials, acceptance testing, and the high cost of thrusters.  Also, the CTE and thermal conductivity of the proposed CICPM can be tailored for a variety of other thermal management applications of interest to NASA.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed technology will find commercial adoption for non-NASA thermal management applications like encapsulating, coating, and/or potting of hot components, subassemblies, and surfaces in high-temperature environments for gas turbine engines, furnaces, processing equipment, aerospace, and automotive. It will be sold through internet distributors and/or through existing distribution channels.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z3.04-5654
SUBTOPIC TITLE:
 Autonomous Modular Assembly Technology for OSAM
PROPOSAL TITLE:
 Autonomous Docking Operations For A Novel In-Space Assembly Connector
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Spaceworks Engineering, Inc. (SEI)
1050 Crown Pointe Parkway, Suite 1400
Atlanta, GA 30038
(770) 379-8007

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Darshan Shah
E-mail:
darshan.shah@spaceworks.aero
Address:
1050 Crown Pointe Parkway, Suite 1400 Atlanta, GA 30338
Phone:
(770) 379-8008

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
John Bradford
E-mail:
john.bradford@spaceworks.aero
Address:
1050 Crown Point Parkway, Suite 1400 Atlanta, GA 30338 - 4747
Phone:
(770) 379-8007
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

SpaceWorks Enterprises, Inc. (SEI) seeks NASA support for the development of a “smart” docking connector for autonomous dock sequencing on a pair of androgynous spacecraft connectors.  The “smart” features on the pair of spacecraft connectors includes a sensing and short-range communication technology that will offer navigational information, handshaking, and auto-dock sequencing during proximity operations and docking between the host spacecraft and target spacecraft. As envisioned, once the enhancements through hardware and software are implemented on the connector system an operational capability is offered to help assist the construction of large spacecraft structures or offer upgradeable modular platforms to existing spacecraft structures. The scope of the Phase I effort includes the study and simulation of proximity operations and the benefits that can be added with a “smart” docking connector configuration. This activity will leverage SpaceWorks' existing, novel connector solution, dubbed FuseBlox™, to create a new autonomous docking system and capability.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Applications that involve the development of a very large spacecraft architectures in GEO orbit and beyond can directly benefit from this development.  Such applications include, but are not limited too, the following: Lunar Gateway initiative, large space telescopes (such as iSAT), and deep space missions that require a large support system for human transport.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The Air Force and DARPA have been actively pursuing robotic in space assembly and servicing. AFSPC SMS effort has recognized the need for modular hardware and the ability to connect, disconnect and re-connect hardware blocks or assemblies on orbit. Commercial entities such as Intelsat and SES could also use this connector for persistent/modular GEO platform system architectures.

Duration: 6

PROPOSAL NUMBER:
 20-1- H4.05-5107
SUBTOPIC TITLE:
 Liquid Cooling and Ventilation Garment Connector Upgrade and Glove Humidity Reduction
PROPOSAL TITLE:
 Next-Generation Self-Healing Lubricants for Liquid Cooling and Ventilation Garment Connectors
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Nanosonic, Inc.
158 Wheatland Drive
Pembroke, VA 24136
(540) 626-6266

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Vince Baranauskas
E-mail:
vince@nanosonic.com
Address:
158 Wheatland Drive Pembroke, VA 24136 - 3645
Phone:
(540) 626-6266

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Melissa Campbell
E-mail:
mcampbell@nanosonic.com
Address:
158 Wheatland Drive Pembroke, VA 24136 - 3645
Phone:
(540) 626-6266
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Through the proposed SBIR program, NanoSonic will design and empirically optimize self-healing microparticles that significantly extend the lifetime of silicone lubricants used within liquid cooling and ventilation garment connectors. NanoSonic’s lubricant filled microcapsules will be precisely tailored for direct compatibility within existing silicone lubricants used by team member ILC Dover and have highly elastic silicone shells that are empirically optimized to gradually break down and release highly dispersible silicone oil into existing seal and gasket greases slowly over extended, simulated tribological wear cycles. The proposed effort will directly build from NanoSonic’s self-healing coating microcapsules and have direct commercial scalability using established oil-in-water suspension polymerization reactions. In support of a low-risk Phase III transition, the proposed self-sealing HybridSil® microcapsules will be intrinsically designed for near term 55-gallon production quantities within an established manufacturing infrastructure.

 

NanoSonic’s lubricant filled microcapsules will directly build from its established self-healing polymeric capsule materials. This capsule technology was uniquely tailored to provide aerospace topcoats a mechanism to autonomously heal themselves from laceration, puncture, and abrasion threats in addition to having long-term environmental durability. NanoSonic is currently working to transition this technology to multiple defense prime and government groups for direction integration into polyurethane aerospace topcoats such as MIL-PRF-85285E. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Building from a successful Phase I effort, NanoSonic will use a Phase II program advancement to further optimize and commercially transition its self-healing microcapsules for LCVG connectors. Working with ILC Dover, numerous additional NASA applications will be pursued including docking systems and vehicle hatches within current and future space vehicles.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Non NASA applications include a broad spectrum of aircraft and aerospace seals numerous applications including engines, landing gear, and flight controls.

Duration: 6

PROPOSAL NUMBER:
 20-1- S3.06-5609
SUBTOPIC TITLE:
 Thermal Control Systems
PROPOSAL TITLE:
 Advanced Survivable Thermal Control Material Systems for Aggressive Planetary Dusty Environments
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Applied Material Systems Engineering, Inc. (AMSENG)
2309 Pennsbury Court
Schaumburg, IL 60194-3884
(312) 498-9673

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mukund Deshpande
E-mail:
m.deshpande@amseng.net
Address:
2309 Pennsbury Court Schaumburg, IL 60194 - 3884
Phone:
(630) 372-9650

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mukund Deshpande
E-mail:
m.deshpande@amseng.net
Address:
2309 Pennsbury Court Schaumburg, IL 60194 - 3884
Phone:
(630) 372-9650
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Abs

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

NASA Science Mission Directorate (SMD) missions can greatly benefit from this dust mitigation thermal coating technology: all lunar-relating project - Power and Thermal Bus Sub Systems, and all projects involved with robotic science rovers and landers.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The Technology Developed can be useful for:

  • Survivable Thermal Control Material Systems, Films & Adhesives that are hardened for the upper atmospheric man made or natural Nuclear Event
  • Solar Storms and GEO, MEO & LEO survivable Products that can employ electron on demand strategies in products like: Hardened Thin Film Products, Wiring harnesses, Balloons
Duration: 6

PROPOSAL NUMBER:
 20-1- A1.09-5690
SUBTOPIC TITLE:
 Inflight Icing Hazard Mitigation Technology
PROPOSAL TITLE:
 Low Power Rechargeable Anti-Icing System for Urban Air Mobility Vehicles
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Innovative Dynamics, Inc.
2560 North Triphammer Road
Ithaca, NY 14850
(607) 257-0533

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Joseph Gerardi
E-mail:
jg@idiny.com
Address:
2560 North Triphammer Road Ithaca, NY 14850 - 9726
Phone:
(607) 591-1742

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Patricia Stein
E-mail:
patricia@idiny.com
Address:
2560 North Triphammer Road Ithaca, NY 14850 - 9726
Phone:
(607) 257-0533
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Next-generation Urban Air Mobility vehicles will require All Weather Capability, including flight into known icing conditions. Ice or frost build-up on propeller surfaces decreases aerodynamic efficiency, resulting in loss of lift when even a small amount of ice builds on rotor-blade surfaces. This can lead to the loss of the aircraft in just minutes. Electrically powered quad-copters have no viable ice protection options today, primarily due to power and weight limitations.

 

IDI proposes development of a Low Power Anti-Icing System specific for short range, short endurance UAM missions. The proposed approach will feature a fast response icing sensor combined with a unique Rechargeable Rotor-Blade Anti-Icing System utilizing smart materials and embedded energy storage components that can be pre-charged independent of the UAM main battery pack. Unique to this design is the ability to wirelessly recharge the rotor de-ice system at electric vehicle docking stations using inductive coupling during scheduled UAM battery pack recharge cycles. 

During the Phase I Program IDI will develop a rechargeable ice protection system design and power management strategy. A prototype will be demonstrated in the Penn State AERTS Rotor Blade Icing Test Facility. Phase II will continue the development and test on a full scale UAM.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

This research supports NASA’s goal to develop icing hazard mitigation technologies necessary for integrating UAS into the National Airspace System. The resulting system could be used to help support various ongoing icing research programs in the NASA Glenn Icing Tunnel and on NASA’s Icing Research Aircraft.

 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The Low Power Anti-Icing System can be applied on commercial quad-copter propellers for flight in instrument meteorological conditions. A wireless rechargeable deicer could be sold as a self-contained feature of next generation propellers. The low-power light-weight requirements give it a significant market advantage over current systems.

Duration: 6

PROPOSAL NUMBER:
 20-1- H6.04-5764
SUBTOPIC TITLE:
 Model Based Systems Engineering for Distributed Development
PROPOSAL TITLE:
 ModelCenter MBSE for OpenMBEE: MBSE Analysis integration for Distributed Development
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Phoenix Integration
1715 Pratt Drive, Suite 2000
Blacksburg, VA 24060
(540) 961-7215

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Andy Ko
E-mail:
ako@phoenix-int.com
Address:
1715 Pratt Drive, Suite 2000 Blacksburg, VA 24060 - 6472
Phone:
(540) 961-7215

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ms. Robin Campbell
E-mail:
rcampbell@phoenix-int.com
Address:
1715 Pratt Drive, Suite 2000 Blacksburg, VA 24060 - 6472
Phone:
(540) 961-7215
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

MBSE has been increasingly embraced by both industry and government to keep track of system complexity. It allows the engineer to represent the system in a comprehensive computer model allowing for better traceability, tracking, and information consistency. The vision and promise of MBSE is one where systems models and analyses are tightly integrated in an automated, collaborative, easily accessible and secure framework. However, the current state-of-the-art falls short of this promise due to a significant gap between MBSE tools and its integration with analysis tools. Phoenix Integration proposes to develop and prototype a framework that would help realize the vision and promise of MBSE. This prototype framework will be web-based, utilizing existing tools and frameworks already deployed and being used at NASA. At the center of the framework is the connection between OpenMBEE and ModelCenter® MBSE. OpenMBEE is an open source collaboration environment for engineering models. It is driven by models and capabilities that support a model-based approach. ModelCenter® MBSE on the other hand, is a next generation MBSE analysis integration tool currently being commercially developed at Phoenix Integration. This framework will be connected to a continuous integration server for automated execution in response to a model change. In addition to being able to interact with the systems model through a web environment, the user would be able to execute the associated analyses and workflows using information from the systems model. Automatic requirements verification can be performed through automated analysis execution whenever a change in the systems model is detected. The analysis that is run can also be represented back in the systems model for full traceability.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

These capabilities will directly benefit ongoing and future NASA projects, such as the Europa Clipper and Lander missions, the Team X and related collaborative design teams, as well as all future science missions. NASA would be able to leverage this technology on any project that involves a significant level of technical and programmatic complexity. This includes most of NASA's commercial lunar lander initiative, various aircraft technology initiatives, as well as planetary exploration missions. 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

This technology will benefit all programs adopting MBSE, including those at the Department of Defense. Commercial organizations such as Lockheed Martin, Northrop Grumman, and Boeing will also benefit as they implement MBSE activities. Other industries such as automotive, pharmaceutical and manufacturing could take advantage of the innovative technology developed here.

Duration: 6

PROPOSAL NUMBER:
 20-1- A1.01-5804
SUBTOPIC TITLE:
 Aeroelasticity and Aeroservoelastic Control
PROPOSAL TITLE:
 Aeroelasticity and Aeroservoelastic Control
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
M4 Engineering, Inc.
4020 Long Beach Boulevard
Long Beach, CA 90807
(562) 981-7797

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Myles Baker
E-mail:
mbaker@m4-engineering.com
Address:
4020 Long Beach Boulevard Long Beach, CA 90807 - 2683
Phone:
(562) 305-3391

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Kevin Roughen
E-mail:
kroughen@m4-engineering.com
Address:
4020 Long Beach Boulevard Long Beach, CA 90807 - 2683
Phone:
(562) 981-7797
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

While advances have been made in the application of computational fluid dynamics (CFD) tools to the aeroelastic and aeroservoelastic analysis of flexible flight vehicles, during the design phase, unsteady lifting surface methods based on the doublet-lattice method or the harmonic gradient method are still the dominant tools used.  We propose a tool that would (1) be at least as accurate as current lifting surface tools in the flight regimes where they are known to be valid, (2) offer a solution across the Mach regime from subsonic to moderately supersonic (Mach 3 or so), (3) capture the fundamental physics of shocks in the transonic regime, (4) have a comparable computational cost to lifting surface/panel codes, and (5) be integrated with standard aeroservoelastic analysis and design tools.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Potential NASA applications will include the use of the developed technology for design of any new generation aircraft or RLV system including complex and novel configurations such as blended wing-bodies, truss-braced wing configurations, low-boom supersonic configurations, etc.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

This technology is expected to have commercial applications to aircraft design of subsonic transports, supersonic vehicles, bombers, fighters, UAV’s, and general aviation airplanes.  As such, it is expected to have significant commercial applications in airplane structural design, primarily with DoD, NASA, and the prime contractors.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z1.05-5805
SUBTOPIC TITLE:
 Lunar & Planetary Surface Power Management & Distribution
PROPOSAL TITLE:
 A Modular, High-Efficiency, Radiation-Hardened, DC-DC Converter with Decentralized Control
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Tallannquest
538 Haggard Street, Suite 406
Plano, TX 75074
(214) 554-2752

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Anton Quiroz
E-mail:
anton@apogeesemi.com
Address:
1013 Hailey St West Melbourne, FL 32904 - 8207
Phone:
(214) 554-2752

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Anton Quiroz
E-mail:
anton@apogeesemi.com
Address:
1013 Hailey St West Melbourne, FL 32904 - 8207
Phone:
(214) 554-2752
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

We propose to develop a power conversion architecture capable of operating at high power (>100 kW) in high-radiation environments and extreme temperatures.  The proposed system is modular, thus providing an array of benefits, including improved thermal management, radiation hardness, and reliability.  The innovations that enable this advantageous architecture are (a) proprietary radiation-hard integrated circuit technology under development at Apogee Semiconductor that permits far more sophisticated control than state-of-the-art radiation-hard ICs, and (b) a novel control architecture that ensures proper power sharing among converter modules without centralized communication, thereby allowing for high modularity and elimination of points of global failure. 

By the end of Phase I, we will have designed and prototyped a set of power converter modules capable of decentralized current sharing at a power level (per module) appropriate to scale up to a full system.  The scale model will operate at below 10 kW but will demonstrate robust decentralized control, high power density/efficiency, and low thermal impedance.  Accomplishing this objective will require system specification through research, analysis, and simulation prior to prototyping. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Power distribution and conversion solutions for lunar and Mars bases.

These modules can also expand the NASA Advanced Modular Power Systems (AMPS) roadmap.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Commercial GEO satellite applications.

Lunar bases proposed by commercial companies such as SpaceX.

Duration: 6

PROPOSAL NUMBER:
 20-1- S2.03-4652
SUBTOPIC TITLE:
 Advanced Optical Systems and Fabrication/Testing/Control Technologies for EUV/Optical and IR Telescope
PROPOSAL TITLE:
 Programmable Phase Nulling Interferometer
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Boulder Nonlinear Systems, Inc.
450 Courtney Way, Unit 107
Lafayette, CO 80026
(303) 604-0077

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Janelle Shane
E-mail:
jshane@bnonlinear.com
Address:
450 Courtney Way, Unit 107 Lafayette, CO 80026 - 8878
Phone:
(303) 604-0077

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mark Tanner
E-mail:
mtanner@bnonlinear.com
Address:
450 Courtney Way, Unit 107 Lafayette, CO 80026 - 8878
Phone:
(303) 604-0077
Estimated Technology Readiness Level (TRL) :
Begin: 4
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

Laser interferometers are the state of the art for characterizing large telescope optics, manufacturing custom optics, aspheres, freeform optics, and for semiconductor wafer characterization. For test optics with large surface errors, a reference optic and/or a custom computer-generated hologram (CGH) can be used to bring the errors within the interferometer’s range.

However, many situations result in large departures from reference optics. Thermal & gravity sag effects in large optics can cause significant deviations, only some of which may be predictable. Test optics in semiconductor manufacturing may include sharp, irregular steps of many waves. In the early stages of optics polishing, departures from reference can be extreme. Custom optics, including asphere and freeform, can deviate hugely from spherical, and for these a custom CGH (with a typical lead time of 6 months and cost of $10k) is not always economical.

We propose to extend the range of an interferometer by providing > 50 waves of programmable phase control using a Spatial Light Modulator (SLM). In addition to extending the range of phase errors that can be characterized, the SLM interferometer can apply additional arbitrary phase.

In Phase I we will upgrade a prototype SLM interferometer that we previously used to demonstrate nulling and programmable phase control. Phase I will focus on improving interferometer speed, calibration, and stability, and quantifying performance through the following technical objectives:

  1. Design for interferometer upgrade with polarization camera
  2. Construction of the SLM interferometer
  3. Implementation of single-shot phase shifting interferometry (PSI)
  4. 2D Phase/voltage SLM calibration
  5. Characterizing range and accuracy
  6. Demonstrating key applications
  7. Delivery & demonstration of Phase I prototype

 

In Phase II BNS will incorporate an upgraded 1536x1536 pixel MacroSLM into a commercial interferometer and demonstrate its performance in typical use cases.

 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

An extended-range interferometer allows measurement of the phase errors of large telescope optics under conditions for which there is no reference available – such as the presence of thermal changes and gravity sag. This could also allow characterization earlier in the polishing process, lowering their overall cost.

The SLM interferometer can also add arbitrary phase, enabling new techniques for retrieving phase error and other mirror characteristics, and testing phase functions from simulation.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The SLM interferometer can save optics manufacturers, especially free-form optics, time and money during manufacturing, since a greater interferometer range will mean optics can be characterized earlier in the fabrication process when their deviations from reference can be large. It can also allow spherical references or existing CGHs to be used for a wider range of optic designs.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z10.04-4678
SUBTOPIC TITLE:
 Manufacturing processes enabling lower-cost, in-space electric propulsion thrusters
PROPOSAL TITLE:
 Innovations in Hollow Cathode Construction Technology
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
E-beam, Inc.
21070 Southwest Tile Flat Road
Beaverton, OR 97007
(503) 628-0703

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Bernard Vancil
E-mail:
bernie@ebeaminc.com
Address:
21070 Southwest Tile Flat Road Beaverton, OR 97007 - 8739
Phone:
(503) 628-0703

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Bernard Vancil
E-mail:
bernie@ebeaminc.com
Address:
21070 Southwest Tile Flat Road Beaverton, OR 97007 - 8739
Phone:
(503) 628-0703
Estimated Technology Readiness Level (TRL) :
Begin: 4
End: 6
Technical Abstract (Limit 2000 characters, approximately 200 words)

We offer several innovations in the joining of various elements in hollow cathodes and the surrounding structures. These replace the more expensive, less compact, brazing technology and mechanical capture currently used. The proposed techniques include welding 1) molybdenum to molybdenum; 2) molybdenum and molybdenum alloys to porous tungsten; 3) molybdenum to stainless steel; 4) molybdenum to kovar; 5) a new potted tungsten heater to cathodes and supports; and 6) alternative materials such as niobium and hafnium. All of these weld processes allow automated production.

 

E beam has over 30 years’ experience developing new, innovative cathode structures. It is the leader in cathode miniaturization. Precision laser and resistance welding is essential for these structures. E beam is the only company that can reliably weld impregnated cathodes to base metals.

 

The secret to successful welding of disparate refractories is the choice of interface materials and the allowance for mismatches in the coefficient of thermal expansion. We routinely employ TIG, resistance, and laser welding in cathode production, and have done ebeam welding.

 

In addition to conventional hollow cathodes, we plan to apply the new joining techniques to scandate hollow cathodes, hollow reservoir cathodes, and planar micro-thruster cathodes. The proposed innovations will improve and lower the cost of conventional hollow cathodes. A planar 0.050-inch diameter planar scandate cathode using heater power of only half a watt is able to produce over one ampere of discharge current.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The innovations apply to NASA’s Hall and ion thrusters that employ conventional impregnated cathodes. These cathodes will be more compact, use less power, be more manufacturable and reliable. For long-range space missions, hollow reservoir cathodes provide longer life than impregnated cathodes. The improvements here will improve the reliability of reservoir cathodes. NASA has several initiatives involving micro-thrusters. The weld technology proposed is critical for  very small planar scandate cathodes capable of  up to 4A of discharge.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The innovations proposed here would apply to hollow cathodes, including reservoir cathodes used in orbit-raising of heavy communications satellites. They also apply to micro-thrusters for SmallSats and CubeSats, where much commercial work is occurring.

Duration: 6

PROPOSAL NUMBER:
 20-1- Z3.05-4692
SUBTOPIC TITLE:
 Satellite Servicing Technologies
PROPOSAL TITLE:
 Miniature Optical Proximity Sensor
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
RC Integrated Systems, LLC
20100 South Western Avenue, Suite A5
Torrance, CA 90501
(760) 383-1218

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Naibing Ma
E-mail:
nma.risl.llc@gmail.com
Address:
20100 South Western Ave, STE A5 Torrance, CA 90501 - 1307
Phone:
(760) 383-1218

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Naibing Ma
E-mail:
nma@rcintegrated.com
Address:
20100 South Western Ave., STE A5 Torrance, CA 90501 - 1307
Phone:
(760) 383-1218
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

To meet the NASA need for low mass low power proximity sensor which can be mounted at the end of a robotic arm, RC Integrated Systems LLC (RISL) proposes to develop a new Miniature Optical Proximity Sensor (MOPS), capable of providing micrometer range resolution for measurement of an arbitrary target ranging from contact to 20cm. This new sensor will achieve over 1 kHz frequency response, consume less than 55mW power, weigh about 7.1 grams, and cost less than 100 dollars. In Phase I, RISL will perform a feasibility study of MOPS through design, modeling and simulation, and laboratory prototype testing to provide evidence that MOPS can meet the NASA requirements. RISL will identify the equipment and resources needed to prototype MOPS, as well as initial MOPS designs and unit cost estimates. In Phase II, RISL will develop the complete MOPS design and refine the design through several iterations to meet all the NASA requirements. Based on iterations of the designs, several generations of the prototypes will be fabricated and tested. In Phase II, performance of the MOPS sensor will be demonstrated through simulated flight tests. A technology readiness level (TRL)-4 and TRL-6 prototype will be demonstrated by the end of Phase I and Phase II respectively.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

MOPS addresses the major NASA requirements of a low mass low power proximity sensor for a robotic arm to enhance satellite servicing. MOPS will for the first time provide a lightweight sensor measuring the distance from the end of the robotic arm to the adjacent free flying satellite which would reduce the risk of a collision or missed capture. It could be applicable to the Restore-L mission as well as other potential servicing missions, platform demonstrations, or smallsats. It could also be applicable to refueling at Artemis.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Military applications include proximity fuzes for a wide range of munitions platforms from 155-mm artillery shells to 40-mm grenades and 30-mm projectiles. Commercial applications include proximity fuzing for nonlethal munitions, which can be attractive for law enforcement organizations. MOPS can also be used for obstacle detection for collision avoidance and facility security.

Duration: 6

PROPOSAL NUMBER:
 20-1- H4.01-5668
SUBTOPIC TITLE:
 Exploration Portable Life Support System Component Challenges
PROPOSAL TITLE:
 Advanced Multipollutant Trace Contaminant Sorbents for the Exploration Portable Life Support System
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Fuel Research, Inc.
87 Church Street
East Hartford, CT 06108
(860) 528-9806

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Marek Wojtowicz
E-mail:
marek@AFRinc.com
Address:
87 Church Street East Hartford, CT 06108 - 3720
Phone:
(860) 528-9806

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Michael Serio
E-mail:
mserio@AFRinc.com
Address:
87 Church Street East Hartford, CT 06108 - 3720
Phone:
(860) 528-9806
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

This proposal addresses the fabrication and testing of structured (monolithic), carbon-based multipollutant trace-contaminant (TC) sorbents for the space suit used in Extravehicular Activities (EVAs). The proposed innovations are: (1) multipollutant trace-contaminant control; (2) thin-walled, structured carbon TC sorbents fabricated using three-dimensional (3D) printing; and (3) the patented low-temperature oxidation step used for the treatment of carbon sorbents. The overall objective is to develop a multipollutant trace-contaminant removal system that is rapidly vacuum-regenerable and that possesses substantial weight, size, and power-requirement advantages with respect to the current state of the art. The Phase 1 objectives are: (1) to demonstrate the effectiveness of monolithic carbon sorbents with respect to ammonia and formaldehyde removal at concentrations much lower than currently demonstrated and tested, i.e. << 20 ppm ammonia and << 3 ppm formaldehyde; (the proposed target is the 7-day Spacecraft Maximum Allowable Concentrations, SMAC); (2) to evaluate the monolithic carbon sorbents with respect to multipollutant TC control, including carbon monoxide and methyl mercaptan; to define a path to sorbent improvements, if needed; and (3) to deliver a sorbent prototype to NASA for further sub-scale testing. This will be accomplished in three tasks: (1) Sorbent Fabrication and Characterization; (2) Sorbent Testing; and (3) Product Assessment.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The main application of the proposed technology would be in spacecraft life-support systems, mainly in extravehicular activities (space suit), but after modifications also in cabin-air revitalization.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The developed technology may find applications in air-revitalization on board US Navy submarines, in commercial and military aircraft, in the future air-conditioning systems for green buildings, and in advanced scuba-diving systems.

Duration: 6

PROPOSAL NUMBER:
 20-1- A2.01-5718
SUBTOPIC TITLE:
 Flight Test and Measurement Technologies
PROPOSAL TITLE:
 Space-Rated, Rugged, Compact and Inexpensive Fiber Sensor Interrogator
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Sensuron, LLC
3101 Bee Caves Road, Suite 110
Austin, TX 78746
(512) 827-2040

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Ben Burns
E-mail:
Ben.Burns@sensuron.com
Address:
3101 Bee Caves rd, Suite 110 Austin, TX 78746 - 5575
Phone:
(512) 827-2040

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Pierrick Vulliez
E-mail:
pierrick.vulliez@sensuron.com
Address:
3101 Bee Caves rd, Suite 110 Austin, TX 78746 - 5575
Phone:
(775) 830-2059
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Fiber optic sensing (FOS) technology is continuously being developed and offers many advantages over other traditional sensing technologies. The fiber sensors are compact, flexible, lightweight, and immune to electromagnetic interference. For optical frequency domain reflectometry (OFDR) interrogation, thousands of Fiber Bragg gratings can be continuously spaced along the length of the fiber to allow for simultaneous measurements of temperature and strain with high spatial resolution. However interrogators implementing OFDR remain costly and are still economically difficult to justify for broad deployment. For this reason, Sensuron is excited to collaborate with NASA in this program to develop and create the technology needed to drive down the cost of this sensing solution and produce a ruggedized low SWAP-C FOS system that will be applicable to temperature and liquid level monitoring applications. The resulting product will be designed to meet harsh environmental specifications for radiation, temperature, shock & vibration as well as humidity. It will be capable of deployment in space missions but its commercial use will be most prevalent across many earth-bound applications.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Cryogenic tanks liquid level sensing

Pressure vessels temperature sensing and structural health monitoring

In-space structural health monitoring of buildings and assets

 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Aerospace: Distributed load monitoring, SHM and failure prediction, composite materials manufacturing and embedment.

Energy: Oil well health equipment monitoring, storage tank liquid level and stratification, wind turbine blade testing.

Automotive: Structural integrity study of prototypes, battery cells temperature monitoring.

Civil engineering: Structural health monitoring of buildings and bridges.

 

 

Duration: 5

PROPOSAL NUMBER:
 20-1- S2.04-4795
SUBTOPIC TITLE:
 X-Ray Mirror Systems Technology, Coating Technology for X-Ray-UV-OIR, and Free-Form Optics
PROPOSAL TITLE:
 High-Speed, Mode-Hop Insensitive SCI Source for Low Coherence Wavefront Probe for Nanometer Level Free-Form Metrology
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Apre Instruments, LLC
2440 West Ruthrauff Road, Suite 100
Tucson, AZ 85745
(860) 398-5764

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Thomas Stalcup
E-mail:
tstalcup@apre-inst.com
Address:
2440 West Ruthrauff Road, Suite 100 Tucson, AZ 85745 - 1950
Phone:
(520) 639-8195

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Robert Smythe
E-mail:
Robert@Apre-Inst.com
Address:
2440 West Ruthrauff Road, Suite 100 Tucson, AZ 85745 - 1950
Phone:
(860) 398-5764
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

Free-form optics promise improved optical system performance in all areas of imaging and illumination optics. Metrology tools with sufficient accuracy  and manufacturing throughputs are limiting the adoption of free-form optics and their advantages, including meeting NASA’s goal of free-form X-Ray optics. The low coherence probe has demonstrated the potential to provide the metrology required but in order to increase the effective data rate new sources are desired. In this proposal we address this problem by introducing a new, mode hop insensitive source which would increase the acquisition rate by three orders of magnitude and simultaneously lower the cost. A free-form probe equipped with this new generation of sources would be able to effectively compete with full field interferometry at the same time bypassing a lot of its disadvantages.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Free-form optics enable small and lightweight imaging and projection optical systems required by NASA. Future NASA missions with alternative low-cost science and small-sized payloads are constrained by the traditional optics. These could benefit greatly by free-form optics as they provide superior imaging and lightweight components to meet the mission requirements. This application aims to enable those optics to be manufactured to the required tolerances (impossible today) to enable free-form optics to be used as envisioned.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Free-form optics in non-NASA applications is limited by the lack of high performance metrology. Cell phones, tablets, computers, remote cameras, machine vision, security and defense, and illumination systems will benefit from free-forms with smaller packaging, lighter weight and better imaging qualities. This technology, precision metrology, promises to make free-form optics commercially viable.

Duration: 6

PROPOSAL NUMBER:
 20-1- S5.06-4808
SUBTOPIC TITLE:
 Space Weather R2O/O2R Technology Development
PROPOSAL TITLE:
 Space Weather Forecasting Toolset to Support Operations
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
CFD Research Corporation
701 McMillian Way Northwest, Suite D
Huntsville, AL 35806
(256) 726-4800

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Vladimir Kolobov
E-mail:
vik@cfdrc.com
Address:
701 McMillian Way Northwest, Suite D Huntsville, AL 35806 - 2923
Phone:
(256) 726-4800

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Silvia Harvey
E-mail:
proposals-contracts@cfdrc.com
Address:
701 McMillian Way Northwest, Suite D Huntsville, AL 35806 - 2923
Phone:
(256) 726-4858
Estimated Technology Readiness Level (TRL) :
Begin: 4
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

Space weather phenomena such as solar flares, coronal mass ejections, and associated solar particle events (SPEs) can damage critical space-based and terrestrial infrastructure. Operators of such systems are in critical need of a capability to forecast major space weather storms and potential effects towards risk mitigation. Currently available tools are research-oriented and may not be suitable for operational use. CFD Research and the University of Alabama in Huntsville propose to develop a novel Radiation, Interplanetary Shocks, and Coronal Sources (RISCS) toolset by enhancing and integrating existing research codes into a software product for situational assessment and decision making related to space operations. Key technology features and innovations include: (1) efficient coupling between component codes that describe inner heliosphere and transport of solar energetic particles; (2) modularity via standardized interfaces for data exchange and user interfaces; (3) development in consultation with NASA and selected end users; (4) improved component codes numerical and physics models; (5) customized configuration of final product for transition to end user operations (R2O/O2R). In Phase I, we will (1) identify potential ends users and technology transition avenues; (2) derive RISCS design requirements t for operational use; (3) characterize features, performance, and limitations of existing space weather modeling software; (4) enhance RISCS toolset via improved interfaces for data exchange, user input, etc.; (5) demonstrate operational performance of a toolset prototype and derive plans for continued R2O/O2R. During Phase II, we will improve component codes numerical/physics models, extensively test RISCS to improve error detection and handling, demonstrate modularity via swap-out of component codes, run end-to-end simulations of the modular code to demonstrate that RISCS meets the specified design requirements, customize and deliver RISCS to selected end user.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

This topic directly addresses NASA’s R2O/O2R responsibilities outlined in the NSWAP, specifically their goal to understand the Sun and its interactions with Earth, including space weather. It also supports NASA SMD’s goal to coordinate efforts to prepare the nation for space weather events, and is aligned with Technology Roadmap TA-11 (11.2.0 on Modeling). The developed RISCS toolkit will support mission operations by forecasting all-clear periods and the occurrence and effects of SPEs to allow implementation of mitigation solutions.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

A predictive capability for SPE-induced radiation and resulting operational effects can help mission/equipment managers schedule tasks and adopt risk mitigation strategies. Directly relevant to DoD agencies and commercial entities with space-based or high-altitude assets (e.g., satellites), commercial aviation, navigation/GPS, radio communications, utilities/power transmission, oil pipelines.

 

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.09-4863
SUBTOPIC TITLE:
 Cryogenic Systems for Sensors and Detectors
PROPOSAL TITLE:
 Ultralight Dewar
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Gloyer-Taylor Laboratories, LLC
112 Mitchell Boulevard
Tullahoma, TN 37388
(931) 455-7333

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Zachary Taylor
E-mail:
zachary.taylor@gtlcompany.com
Address:
41548 Eastman Drive Unit A Murrieta, CA 92562 - 7051
Phone:
(951) 600-9999

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Paul Gloyer
E-mail:
paul.gloyer@gtlcompany.com
Address:
112 Mitchell Boulevard Tullahoma, TN 37388 - 4002
Phone:
(931) 455-7333
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

GTL’s ultralightweight BHL™ dewar provides dramatically reduced mass, and increased performance over metal dewars. In cryogenic propellant storage systems, BHL has a demonstrated mass reduction of 75%. A similar mass reduction is expected for dewar applications. BHL allows thinner carbon fiber plies to be used, reducing mass and thermal mass while also increasing thermal resistance. Varying materials can be used throughout the structure to optimize for liquid helium storage.

The GTL team is extensively experienced in cryogenic isolation, dewar production, composites manufacturing, and cryogenic fluid testing. GTL is currently producing 4 ft diameter cryogenic structures and has existing designs for integrated dewar systems. This phase I and II effort will conclude at a high TRL, ready for phase III application, due to the experience and capability of GTL.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The BHL technology applied to dewar systems offers significant improvements over current state-of-the-art dewars. BHL will provide for reduced boil-off, reduced cost, and easier transport of the dewars. BHL dewars could be applied to a large number of NASA systems. Anywhere cryogenic fluid is stored could potentially be replaced with these low mass, high efficiency composite dewars. NASA space systems, lunar and Mars landers, lunar and Mars habitats, as well as long term storage could benefit greatly from low mass BHL dewars and/or cryotanks.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

For the same reasons that these composite dewars would be so beneficial to NASA, they would also be beneficial to the DoD. These low mass dewars could enable aircraft to run off of other fuels, such as liquid natural gas and liquid hydrogen. In the private sector BHL cryogenic dewars could be implemented in hospitals, research corporations, and cold gas/welding suppliers.

Duration: 6

PROPOSAL NUMBER:
 20-1- S1.11-4876
SUBTOPIC TITLE:
 In Situ Instruments/Technologies and Plume Sampling Systems for Ocean Worlds Life Detection
PROPOSAL TITLE:
 Polarimetric Detection of Agnostic Chiral Biosignatures
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Sparks Polarimetry, LLC
18124 Gunpowder Road
Hampstead, MD 21074
(443) 244-3332

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. William Sparks
E-mail:
william.b.sparks@sparkspolarimetry.com
Address:
18124 Gunpowder Road Hampstead, MD 21074 - 2912
Phone:
(443) 244-3332

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. William Sparks
E-mail:
william.b.sparks@sparkspolarimetry.com
Address:
18124 Gunpowder Road Hampstead, MD 21074 - 2912
Phone:
(443) 244-3332
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

We propose to validate an innovative spectropolarimeter which is exceptionally sensitive to circular polarization. The polarimeter is small and robust, has no moving parts, is simple in concept and extremely well-suited to space. Full polarimetric information is encoded on a single data frame hence polarimetry of transient, fast moving or variable targets can be acquired.

The goals of Focus Area S1.11 In Situ Instruments/Technologies and Plume Sampling Systems for Ocean Worlds Life Detection are to advance science instruments focused on the detection of life, especially extant life in the Ocean Worlds, including innovative new scientific measurements. Our proposed polarimeter with its exceptional circular polarization measurement capability has particular relevance to these goals.

Circular polarization serves as a pure agnostic biosignature, symptomatic of the uniquely biological phenomenon of homochirality. S1.11 seeks “Life detection approaches optimized for evaluating and analyzing the composition of ice matrices with unknown pH and salt content. Instruments capable of detecting and identifying organic molecules (in particular biomolecules), … such as … organic analysis instruments with chiral discrimination.” Circular polarization spectroscopy is sensitive to any chiral structures, including those of amino acids, proteins and more, without specificity, hence provides a truly generic, agnostic life detection capacity.

The instrument’s optimal response to circular polarization leads to mission relevant sensitivity for life detection. Dissolved salts and pH level have no influence. The polarimeter simultaneously and independently measures circular and linear polarization hence offering a powerful tool for the characterization of surfaces and particles with implications for habitability.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

In situ life detection capability relevant to Ocean Worlds missions such as the Europa Lander

In situ life detection for Ocean World plume fly-through samples, in particular Enceladus and Europa

Remote sensing for life detection, habitability and physical characterization in solar system exploration in general.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Versatility and low cost provides opportunity in the private space sector.

Sensitivity to circular polarization leads to application in the biological sciences: medicine, pharmacy, agriculture.

Polarimetry of time dependent phenomena enables application in physics and biology.

Education is a major commercial opportunity, synergistically building on NASAs mission to search for life in the Universe

Duration: 6

PROPOSAL NUMBER:
 20-1- H12.05-4929
SUBTOPIC TITLE:
 Autonomous Medical Operations
PROPOSAL TITLE:
 Autonomous Medical Response Agent (AMRA) for Prolonged Field Care in Space
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Nahlia Inc
95 1st Street, Suite 240
Los Altos, CA 94022
(310) 936-6237

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Jayant Menon
E-mail:
jayant@nahlia.com
Address:
95 1st Street, Suite 240 Los Altos, CA 94022 - 2765
Phone:
(310) 936-6237

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Jayant Menon
E-mail:
jayant@nahlia.com
Address:
95 1st Street, Suite 240 Los Altos, CA 94022 - 2765
Phone:
(310) 936-6237
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Prolonged Field Care (PFC) is utilized by the US Military to deliver field medical care beyond planned timelines of evacuation in order to decrease patient mortality and morbidity. PFC utilizes limited resources to sustain care until the patient arrives at the next level of care.  Life-threatening medical conditions requiring evacuation, pose a significant risk of loss of life and mission for long duration exploration missions  Astronaut crews evacuating to earth will deliver prolonged field care without real-time decision support. NASA will need to   develop prolonged field care protocols that incorporate autonomous decision support. 

Nahlia Inc demonstrated an Autonomous Medical Response Agent (AMRA) in previous research efforts. AMRA is a multi-criteria feedback control Bayesian clinical decision support tool. Clinical history, physical exam, laboratory and imaging assessments, vehicle and environmental data are combined. Calculated post-test likelihood distributions of disease, clinical and mission outcomes (Med09) guide the sequence of evidence-based protocols. Inventory and astronaut personal preference (Med03) filter choices and just-in-time training provides point-of-care instruction to CMO's. Outcomes measures provide a multi-organ system state estimate of health and contributes to an estimated risk posture for crew and mission (Med08, Med09).  Differences between current and goal health state, defined by NASA STD3001, sustain AMRAs guidance until a goal state is achieved.  AMRA sends information to Mission Control, coordinating asynchronous care (HARI02). 

The proposal seeks to establish the benefits and feasibility of a systematic capability to develop, guide, and train PFC protocols for space. Tasks include (1)systematic approach to evidence-based autonomous PFC protocols  (2) Clinical Case Simulator to test PFC protocols, (3) Mission Coordinator to facilitate collaboration with Mission control 4) Case-Based Trainer to prepare Astronauts for PFC in Space. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

High severity of illness, rapid decision making, where real-time telemedicine support is not available makes Prolonged Field Care scenarios the most likely lead to loss of crew and loss of life on long duration missions. For example: Acute respiratory distress, Undifferentiated Shock, MultiOrgan system Trauma  

Autonomous decision support, proposed here, will be required to support training and guiding Crew Medical Officers performing PFC in space. 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Coordinated Bayesian Decision support can be used to automate the standard of care, decrease cognitive overload in other arenas. Military Prolonged Field Care, Disaster response, rural medical care, pandemic response,

Duration: 6

PROPOSAL NUMBER:
 20-1- Z12.01-4941
SUBTOPIC TITLE:
 Extraction of Oxygen from Lunar Regolith
PROPOSAL TITLE:
 Thermal Management System for Lunar Ice Miners
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Cooling Technologies, Inc.
1046 New Holland Avenue
Lancaster, PA 17601
(717) 205-0602

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Kuan-Lin Lee
E-mail:
kuan-lin.lee@1-act.com
Address:
1046 New Holland Avenue Lancaster, PA 17601 - 5688
Phone:
(717) 205-0631

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
William Anderson
E-mail:
Bill.Anderson@1-act.com
Address:
1046 New Holland Avenue Lancaster, PA 17601 - 5688
Phone:
(717) 205-0602
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

The millions of tons of ice water discovered by the Lunar Crater Observation and Sensing Satellite (LCROSS) mission is considered to be the most valuable resource on the moon. Extracting this water ice from Lunar regolith would require a very high thermal energy input and inversely, capturing this water vapor in the near-vacuum environment also requires significant cooling capacity. Therefore, it is necessary to develop a robust thermal management system (TMS) for future Lunar Ice Mining Rovers that are powered by radioisotopes. Advanced Cooling Technologies, Inc. (ACT), in collaboration with Honeybee Robotics (HBR), proposes to develop a thermal management system that can strategically use the waste heat of nuclear power sources to sublimate water vapor from icy-soil on the moon and use the Lunar environment temperature as the heat sink to refreeze the sublimated vapor within the cold trap container. This minimizes the required electric energy for both ice extraction and vapor collection, with a lower system mass and footprint. In Phase I, ACT/HBR team will perform a detailed trade study and design multiple thermal components of TMS including a waste heat-based thermal coring drill and a heat pipe radiator cold trap tank. A proof-of-concept prototype will be developed and tested in Phase I. A preliminary full-system that can potentially meet NASA’s mining requirement will be designed and evaluated for the mining efficiency, system mass/volume and power consumption (both electrical and thermal).

Duration: 6

PROPOSAL NUMBER:
 20-1- H10.01-5289
SUBTOPIC TITLE:
 Advanced Propulsion Systems Ground Test Technology
PROPOSAL TITLE:
 A Fast and Robust PIMPLE-Based Algebraic VOF Method for Two-Phase Compressible Flows
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Streamline Numerics, Inc.
3221 North West 13th Street, Suite A
Gainesville, FL 32609
(352) 271-8841

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Siddharth Thakur
E-mail:
st@snumerics.com
Address:
3221 North West 13th Street, Suite A Gainesville, FL 32609 - 2189
Phone:
(352) 271-8841

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Jeffrey Wright
E-mail:
jeffwright83@gmail.com
Address:
12017 sw 122nd st gainesville, FL 32608 - 5847
Phone:
(352) 271-8841
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

This project is geared towards a computationally efficient, robust computational fluid dynamics (CFD) tool for simulating unsteady multiphase flows of critical importance to NASA in their ground and launch systems processing technologies.  The key features of the proposed work are: (a) Significant cost reduction in unsteady simulations via the PIMPLE algorithm, and (b) a fast and robust Algebraic Volume of Fluid (AVOF) method for two-phase flows. This methodology will be developed in the Loci-STREAM CFD code and will allow significantly reduced solution time for unsteady simulations of cavitating flows and fluid-structure interaction (FSI) simulations at NASA, as well as simulation of liquid jets and sprays such as in NASA/SSC’s B-2 test facility. The work will involve: (a) upgrading the unsteady methodology in Loci-STREAM by implementing the PIMPLE algorithm, and will improve runtime of cavitation and FSI simulations by a factor of 3–5, and (b) Implementing an algebraic VOF method using compressive schemes which will allow simulations of two-phase flows (involving liquid jets) in a robust and more efficient manner (significantly faster solution times) manner than is currently possible with the geometric VOF available in Loci-STREAM. Two types of compressive schemes will be implemented: (a) Schemes based on the Normalized Variable Diagram (NVD) and Convection Boundedness Criterion (CBC), and (b) Flux-limiting schemes with the total variation diminishing (TVD) condition. The following application areas will benefit immediately from this project: (i) Unsteady cavitation in cryogenic propellant tanks, valve flows, and run lines, (ii) Transient fluid structure interaction (FSI) between cryogenic fluids and immersed components to predict the dynamic loads, frequency response of facilities, and (c) Modeling of liquid (water) jets including their breakup for flow tests on the B-2 test stand to verify the water system capability and functionality in support of the SLS.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)
  1. Modeling of cavitation in cryogenic propellant tanks, valve flows, and run lines
  2. Modeling of transient fluid structure interaction (FSI) between cryogenic fluids and immersed components to predict the dynamic loads, frequency response of facilities
  3. Modeling of water jets for flow tests on the B-2 test stand to verify the water system capability and functionality in support of the SLS
  4. Water deluge mitigation for rocket launch induced environments
  5. Subcritical injector analysis for gas generators, preburners and thrust chambers
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)
  1. Two-phase applications involving non-reacting & reacting flows.
  2. Fast and accurate simulation for reacting flows at companies dealing with space propulsion, gas turbine, diesel engines, etc.
  3. Loci-STREAM code is being used at Aerojet Rocketdyne for gas-gas injector simulations; it’s applicability will be broadened to liquid propellant engines by this project.
Duration: 6

PROPOSAL NUMBER:
 20-1- A3.04-5339
SUBTOPIC TITLE:
 Non-Traditional Airspace Operations
PROPOSAL TITLE:
 Noise-Impacted UAM Flight Path Optimization
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
ATAC
2770 De La Cruz Boulevard
Santa Clara, CA 95050
(408) 736-2822

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Ray Bea
E-mail:
rcb@atac.com
Address:
2770 De La Cruz Boulevard Santa Clara, CA 95050 - 2624
Phone:
(925) 570-3464

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Joe Isaacs
E-mail:
jai@ATAC.com
Address:
2770 De La Cruz Blvd. Santa Clara, CA 95050 - 2624
Phone:
(408) 736-2822
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

NASA’s Parimal Kopardekar has stated on multiple occasions that noise is one of the top three challenges for Urban Air Mobility (UAM). We specifically target developing a software system called the Quiet UAM Impact Path Planning (QUIPP) Tool for generating electric vertical take-off and landing (eVTOL) aircraft flight paths that minimize noise impacts on people within the UAM on-demand environment. This new capability will enhance the A3.04 subtopic’s need for “dynamic route planning that considers changing environmental conditions, vehicle performance and endurance” by developing flight paths based on current noise impacts and constraints within the operating environment, thereby adding agility, scalability, and adaptability to dynamic route planning. The QUIPP system proposed in this SBIR generates 4-dimensional trajectories that are the least intrusive in terms of the overall cumulative noise impacts on the population while considering vehicle endurance such as maximum range. QUIPP comprises dynamic input datasets and flight path optimization that rely on current noise contours from a noise model. The dynamic inputs are used by QUIPP to synthesize noise-sensitive 4-D trajectories by applying an adaptation of Dijkstra's shortest path algorithm to find the lowest cost route. QUIPP will help to gain community acceptance of UAM by developing optimal flight paths that utilize the current noise conditions and the temporal movement of people throughout the day to minimize noise exposure. QUIPP minimizes the noise impact of UAM flights to gain local community acceptance, which is a critical issue to UAM success. The anticipated result of Phase I is successful demonstration of a proof-of-concept where flight paths are developed that minimize the noise impact on the population while working within the boundaries of environmental and aircraft constraints. In addition, QUIPP will demonstrate fast response times needed in an on-demand environment.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

QUIPP can be used (1) for noise-sensitive route optimization algorithm development in NASA’s UAM Noise Working Group, (2) for UAM flight demonstrations/tests by the ATM-X Initial UAM Ops Integration sub-project and Advanced Air Mobility National Campaign, (3) to analyze missions for concept vehicles from the Revolutionary Vertical Lift Technology and Rotorcraft Technology Development sub-projects, and (4) integrated with the ATM-X Testbed to simulate regular or noise-sensitive UAM flight plans.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

QUIPP software can be (1) integrated within existing flight planning software from current vendors such as ForeFlight, (2) integrated into services offered by USSs such as AirMap, (3) used to support urban communities impacted by future UAM flights, and (4) used by stakeholders and operators responsible for UAM noise complaints and compliance with future UAM environmental regulations and policy.

Duration: 6

PROPOSAL NUMBER:
 20-1- A1.10-4992
SUBTOPIC TITLE:
 Hypersonic/High Speed Technology - Seals and Thermal Barriers
PROPOSAL TITLE:
 Ultra-High Temperature Elastomer Sealing Materials
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
ATSP Innovations
60 Hazelwood Drive
Champaign, IL 61820
(217) 778-4400

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Jacob Meyer
E-mail:
jacob.l.meyer@atspinnovations.com
Address:
60 Hazelwood Drive Champaign, IL 61820 - 7460
Phone:
(217) 778-4400

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Jacob Meyer
E-mail:
jacob.l.meyer@atspinnovations.com
Address:
60 Hazelwood Drive Champaign, IL 61820 - 7460
Phone:
(217) 778-4400
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

This proposal addresses subtopic A1.01 Hyersonic/High Speed Technology - Seals and Thermal Barriers, specifically the listed interest in high temperature elastomeric materials for use at temperatures of 700℉ (371 ℃) or greater. O-rings and other low leakage seals are frequently employed in a broad range of industries. These O-rings are frequently used to seal one environment from another especially in mechanical designs incorporating moving components at the interface. As supersonic and hypersonic vehicles increase in importance, materials capable of meeting their demanding applications are sought. Current high temperature elastomers encounter an upper temperature limit near 600℉ - a new material that surpasses this limitation may offer new utility. We propose an oligomeric pre-polymer strategy to synthesize tractable oligomers - a proven technique derivative of ATSP’s core chemical strategy for synthesis of high glass transition temperature aromatic thermosetting copolyester resins but redesigned to incorprate the flexible chains necessary to form an extremely thermally stable new elastomer -offering continuous performance at 700℉ (371℃) and above, thus meeting the high-end requirements for hypersonic vehicles requested in the solicitation.

The synthesized chemistry will be examined via nuclear magnetic resonance. Differential scanning calorimetry (DSC) will then be used to determine a rational thermal cure cycle. Thermal stability will be assessed through thermogravimetry. The combined process cycle will be developed through multiple iterative cycles while being evaluated through density determination and x-ray micro-computed tomography to determine void content and converge on the ideal density in the produced article. Produced articles will be examined in terms of their mechanical properties (including compression set and high temperature aging) as well as their glass transition. A single best-performing composition will be selected for a dynamic sealing test.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Phase I will enable ATSP Innovations and team partner UIUC to acquire the necessary synthetic and processing information to produce the ultra-high temperature elastomers for next-generation performance sealing applications over 700℉, such as for thermal protection system sealing. Hypersonic fuel systems and internal seals, and passive vibration damping components may also benefit. Further application may be found on components of potential future Venus, Mercury, or close-solar-approach missions.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

This project would have impact in next-generation high speed aerospace applications In addition, industrial users may have a faster adoption time and substantial volumes.  Critical uses for this product in these spaces include compressed gas waterless fracking seals; LPG; and liquid nitrogen seals, as well as rotary, reciprocating, and oscillatory motions in those application spaces.

Duration: 6

PROPOSAL NUMBER:
 20-1- S4.02-5011
SUBTOPIC TITLE:
 Robotic Mobility, Manipulation and Sampling
PROPOSAL TITLE:
 Compact, Robust Pump for Deep Subsurface Ice Penetration
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Creare, LLC
16 Great Hollow Road
Hanover, NH 03755
(603) 643-3800

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Thomas Conboy
E-mail:
tmc@creare.com
Address:
16 Great Hollow Road Hanover, NH 03755 - 3116
Phone:
(603) 643-3800

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Robert Kline-Schoder
E-mail:
contractsmgr@creare.com
Address:
16 Great Hollow Road Hanover, NH 03755 - 3116
Phone:
(603) 640-2487
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

NASA is actively considering surface missions to explore planetary bodies that may harbor liquid oceans, such as Europa and Enceladus. While these moons outwardly present an icy surface, scientists believe tidal activity driven by their respective host planets may drive thermal activity beneath, sustaining warm bodies of water that could potentially provide conditions favorable for life. Robotic penetration technologies are needed to drive through the ice layer, enabling access to subsurface oceans for exploration. A leading approach to drilling surface ice for remote space missions involves use of a robotic melt‑probe that would use residual heat from its radioisotope source to supply a warm water jet to accelerate the descent. A critical need for this type of system is a water jet pump that can operate in the extreme inhospitable environment of a deep subsurface ice, while reliably delivering melted ice to the jet nozzle for a long endurance, persistent drilling activity. To meet this need, Creare proposes to develop a robust, miniature, high speed water jet pump, designed for very long service