NASA SBIR/STTR Program Solicitation Details | STTR Research Topics | Modeling And Estimation Of Integrated Human-Vehicle Design Influences

There has been recent significant growth in both the Quantity and Quality of Nano and Micro Satellite Missions:     

• The number of missions has outpaced available ride share opportunities. 
• Dedicated access to space increases small sat mission capability & allows new & emerging low-cost technologies to be flight qualified. 

Stage concepts are sought that can be demonstrated within the scope & budget of a Phase II STTR project:   

• MSFC is actively pursuing multiple technologies to significantly reduce orbital access cost. 
• The scale of many Nano and Micro Launch vehicles allows stages to be completed within the scope and budget of a Phase II proposals.
• Accepted proposals will be limited to stages that plug and play into existing or proposed architectures for orbital launch vehicles with payload capabilities from 5-50 kg. A flight test is expected in Phase II.
• The university/small business partnership is ideal to provide the correct technology combination allowing for this affordable access to space. 

State of the Art 

Small launch vehicles are targeting a total launch cost of ~$1-2M. Proposed stages must demonstrate significant cost savings over state of the art. 

What is the compelling need for this subtopic? 

• This subtopic is necessary because there are currently no available rides for experimental propulsive stages.
• Technological advancements like additive mfg. must be demonstrated to produce aerospace quality parts at low fixed cost. These technologies must be validated for use in propulsive stages.
• The correct combination of new technologies and approaches will enable affordable, dedicated, on-demand access to space.
• Technologies that are demonstrated and validated at the nano/micro scale can be robustly infused into large launch vehicles where loads and vibrations are not as severe.
• The success of Nano/Micro Launch vehicles benefit every NASA center by enabling unprecedented experimental access to space.
• Commercial development opportunities abound since the small satellite market is robust and growing. 

STMD/NASA/NARP/National-Affordable access to space is a key objective for NASA.  The Nano/Micro Launch scale is an affordable avenue that will enable the development and validation of key technologies and approaches to reduce fixed cost, recurring costs and range costs.

Detailed modeling and simulation to assess combustion instability of recent large combustors while successful to a degree showed the need for significant advances in two-phase flow, combustion, unsteady flow, and acoustics.  Additionally, simulation of water spray systems for launch acoustic sound suppression and test stand rocket engine acoustic sound suppression showed the need for advances in two-phase flow, droplet formation, and particulate trajectory.  In these cases, and others, the need for improved physics based models is accompanied by the requirement for high fidelity and computational speed. 

Rocket combustion dynamic simulations are 3D, multiphase, reacting computations involving the mixing of hundreds of individual injection elements which require a long time history to be computed. Methods are sought (VOF, SPH, DNS/LES, PIC, etc.) to accurately capture the physics of the injection elements in a computationally efficient manner. Experimental validation of individual submodels are required. 

NASA successfully leveraged advances/ innovation in computer science technology to leapfrog the barriers to massive parallelism via the adoption of the Loci framework in the late 1990's.  Computer science has evolved in the last two decades with respect to technology of massive parallelism.  The intent of this subtopic is to infuse newest technologies, i.e., improved physics based models accompanied by the requirement for high fidelity and computational speed, into tools for propulsion related fluid dynamic simulation.  This solicitation seeks simultaneously coordinated computer science (CS) technology advances, multi-physics (MP) simulation, and high fidelity (HF) models.  The value and requirement for proposals is this coordinated CS-MP-HF framework.  Ideally, technologies that are up to this point only Lower TRL demonstrations are strong candidates if they are developed to fit in a coordinated CS-MP-HF framework that can be applied to propulsion system fluid dynamics. 

Tools developed in this framework are expected to enable propulsion system production & DDT&E cost reductions.  

The objective of this subtopic is to advance low TRL (<3) nuclear propulsion technologies that have the potential to transform space transportation and space exploration to Mars and other planets/moons in our solar system. Radical improvements in in-space propulsion technologies beyond the current state of the art (SOA) are required to enable new missions that safely transport humans and/or robotic systems with increased reliability to meet mission requirements, transport them quickly to reduce transit times and provide quicker scientific results, increase the payload mass to allow more capable instruments and larger crews, and reduce the overall mission cost. SOA in-space transportation systems typically employ chemical propulsion or electric propulsion systems.  In parallel, thought must go into how best to ground test these concepts to allow a smoother, more efficient and safer path for future development.

This subtopic specifically seeks proposals for innovative research and development of advanced nuclear propulsion technologies that have the potential for significant improvement over the current SOA, primarily to achieve:

• High specific impulse (Isp) and thrust-to-weight ratio (T/W) to consume less propellant and provide shorter trip times.

Other design requirements to consider in the proposed concept include:

• Low system mass and volume (includes propellant, power system, thermal control/radiators) to reduce the total mass and number of launches to orbit.
• Safety, affordability, and reliability

Most of the known advanced nuclear propulsion candidate technologies are listed in the 2015 NASA OCT Roadmap TA02: In-Space Propulsion Technologies (http://www.nasa.gov/offices/oct/home/roadmaps/index.html). Advanced nuclear propulsion technologies are identified in section 2.3.3 Fusion Propulsion, section 2.3.5 Antimatter Propulsion, and section 2.3.6 Advanced Fission. Technology SOA and technical challenges are included for each.

Other advanced nuclear propulsion technologies not listed in the 2015 OCT TA02 Roadmap are welcome and within the scope of the subtopic (e.g., various nuclear hybrid concepts), including novel system and component ground test approaches and associated supporting/enabling technologies.

Proposed technologies must be theoretically credible and proposals must describe how the technology will make a significant improvement over SOA in-space propulsion systems. Proposals must describe the ultimate objective of the effort and detail the planned investigative approach. The planned experimentation should be described, including the test equipment to be used and/or developed. The proposal should describe the development risks and mitigation plans.

Proposals should strive to advance the proposed technology to TRL 3: perform experimental critical function and/or proof-of-concept. If a significant increase in the TRL of a particular propulsion technology is not realizable, the proposal should clearly indicate the value proposition of the proposed effort to mature the candidate technology in the context of an overall development plan, describing how the award would support the maturation of the technology through phase II.

The NRC has identified a NASA Top Technical Challenge as the need to "Increase Available Power". Additionally, a NASA Grand Challenge is "Affordable and Abundant Power" for NASA mission activities. As such, novel energy harvesting technologies are critical toward supporting future power generation systems to begin to meet these challenges. This subtopic addresses the potential for deriving power from waste engine heat, warm soil, liquids, kinetic motion, piezoelectric materials or other naturally occurring energy sources, etc. Development of energy harvesting (both capture and conversion) technologies would also address the national need for novel new energy systems and alternatives to reduce energy consumption.  Conversion and transformation technologies for gathering energy naturally occurring in conjunction with induced energies are being pursued, and novel technologies capable of artificially saturating an environment with energy for storage and power dissemination along with non-conventional transmission via the surrounding environments such as wireless power are also applicable. Energy gathering is limited by the quantity of energy available within a system’s immediate environment, and often the environment’s energy contains prolonged periods of lulls in harvestable energy. Technologically bridging power from a distance would fundamentally alleviate issues with low energy environments by allowing energy to be supplementally broadcast through preexisting structures and environments while simultaneously reducing docking and interfacing for power transfer. 

Technology development should support powering small remotely located equipment such as wireless instrumentation, or support power gathering for independently providing supplementary power to centralized equipment such as control consoles. Distributed Nano energy generating technologies are applicable for gathering scattered environmental energies into significant amounts of accumulated power along with supplementation for long-duration power utilization. This kind of distributed power should also be able to recover waste energy from rocket, nuclear, fission, and electrical propulsion devices while providing enhanced protection from energies contained within the work environment through transformation and consumption.  Transforming harmful radiation, elevated temperatures, unwanted vibrations etc. into usable energy will support increased scope and duration of missions while enhancing protection from the waste energies (mitigation by transformation and consumption). Waste energies from warm soil, liquids (water, oils, hydraulic fluids), kinetic motion, piezoelectric materials, or various naturally occurring energy sources, etc. should also be transformable.  

Areas of special focus for this subtopic include consideration of: 

• Innovative technologies for the efficient broadcast, capture, regulation, storage and/or transformation of acoustic, kinetic, radiant (including radiation), electric, magnetic, radio frequencies and thermal energy types.
• Technologies which can work either under typical ambient environments for the above energy types and/or under high intensity energy environments for the above energy types as might be found in propulsion testing and launch facilities.
• As above, energy capture, transmission and transformation technologies that can work in very harsh environments such as those which are very hot and/or ablative (e.g., in the proximity of rocket exhaust) and/or very cold (e.g., temperatures associated cryogenic propellants) may be of interest.
• Innovations in miniaturization and suitability for manufacturing of energy capture, transmission and transformation systems so as to be used towards eventual powering of assorted sensors and IT systems on vehicles and infrastructures.
• High efficiency and reliability for use in environments that may be remote and/or hazardous and having low maintenance requirements.
• Employ green technology considerations to minimize impact on the environment and other resource usage. 

• Reliable nano-engineered concept designs for generating charge and charge storage devices powering miniature (or “nano”) devices, such as members of a “swarm” are needed for exploration purposes.  Designs should be capable of easy integration to miniaturize systems, subsystems, satellites, or “swarm” elements without compromising capability.
• Designs should maximize high energy density for charge storage with very low mass. 

Rocket propulsion test facilities within NASA provide excellent test beds for testing and using the innovative technologies discussed above because they offer a wide spectrum of energy types and energy intensities for capture and transformation. Additional Federal mandates require the optimization of current energy use and development of alternative energy sources to conserve on energy and to enhance the sustainability of these and other facilities.Specific emphasis is on technologies which can be demonstrated in a ground test environment and have the ability/intention to be extrapolated for in-space applications such as on space vehicles, platforms or habitats. Energy transformation technologies to generate higher power output than what is presently on the market are a highly desired to an expected outcome from this subtopic. 

Phase I will develop feasibility studies and demonstrate through proof-of-concept demonstrations. Phase II will develop prototypical hardware and demonstrate infusion readiness to be incorporated into other products.

Missions to Mars and beyond experience communication delays with Earth of between 3 to 45 minutes.   Due to this, it is impractical to rely on ground-based support and troubleshooting in the event of a power system fault or component failure.  Intelligent/autonomous systems are required that can manage the power system in both normal mode and failure mode.

In normal mode, the system would predict energy availability, perform load scheduling, maintain system security and status on-board and ground based personnel.  One aspect of overall system autonomy would be solar array characterization, for spacecraft utilizing this technology.  One drawback of current satellite systems is the lack of adequate means of determining solar panel or cell status.  Being able to automatically characterize solar panel status can enhance energy availability prediction.  Similar technology to access that status of battery systems would further enhance these predictions.

In failure mode, the system must identify a fault or failure and perform contingency planning to react or reconfigure the system appropriately to move it back into normal mode of operation, without human involvement.   The technologies to detect and identify specific failures in both the generation, distribution and storage systems are needed along with strategies to utilize the failure data to identify recovery strategies for the power system.

With the potential of future manned missions to Mars, this technology will become increasingly important for electrical power management and distribution.   Specific areas of interest include:

• Autonomous/intelligent PMAD.
• Failure detection strategies.
• Recovery strategies.
• Generation and storage characterization.

Nearly all engineered systems in all of NASA's areas of interest have one key aspect in common---they generate substantial data. These data represent:

• Science and scientific applications.
• The operations of the data collecting instruments and their platforms.
• The health of these instruments and platforms.
• In some cases, other related data such as the performance and health of the humans involved in operations.

Machine learning, data mining, big data, and related methods have been used to study data in these four areas individually for offline study, with the goal of understanding how the system really operates, as distinct from how it was designed and intended to operate. However, these data-driven methods have not been used so far to study data across more than one of these four areas, and not during operations, with the goal of enabling a human and/or autonomous system to make adjustments to the system's operations on the fly. Allowing both online and offline learning would allow for both online (tactical) and offline (strategic) adjustments to operations. Allowing humans and autonomous systems to interact in making strategic and tactical decisions, including user interfaces that allow the autonomous system to show the human what it has learned and the human to specify high-level objectives and/or low-level actions, is a key problem to be addressed. Increasing the scope of the data covered to all of the four areas above would allow autonomous systems and human operators to account for both science and system health drivers in operations, and identify the trade-offs between increasing science operations, increasing availability, maintaining systems health, minimizing maintenance costs, and other considerations. Some of these considerations may extend to improvements in on-demand system responsiveness through optimal resource sharing of the computational burden between online and offline computing platforms. Integration of learning autonomous systems into existing mission operations and systems is a key problem that will need to be addressed.

The utilization of the above types of data to optimize all aspects of operations is important for missions/projects in all of NASA's areas of interest such as space science (e.g., Kepler, TESS), space exploration (human and autonomous rovers), Earth science (satellite-based and airborne instruments and platforms), and aeronautics (e.g., UAS in the NAS) to operate them in as cost-effective a manner as possible. This becomes more critical as NASA increasingly moves towards operating multiple platforms in a coordinated manner (e.g., Distributed Spacecraft Missions, airborne Earth science platforms coordinating with satellite instrument platforms) where the volume of relevant data will increase and autonomy will be needed to properly operate the multiple platforms.

This subtopic has three goals:

• Increase the scope of machine learning, data mining, and big data methods within NASA to encompass both online and offline learning.
• Use data across as many of the above four areas of data as possible.
• Explore the trade-offs in operational efficiency, energy efficiency, health management, and operational performance/goal achievement between onboard and offboard computational resource platforms.

Proposed solutions may have characteristics including but not limited to:

• Ability to incorporate human feedback into the learning algorithms.
• Ability for machine learning algorithms to generate results for direct use by autonomous systems and human operators.
• Ability to learn a controller (covering strategic and tactical operations) from data representing human expert operations.
• Demonstration of a core set of tools that works across different domains.

A Distributed Spacecraft Mission (DSM) is a mission that involves multiple spacecraft to achieve one or more common goals; some DSM Instances include Constellations, Formation Flying missions, or Fractionated missions. Apart from Science goals that can only be attained with DSM, distributed missions are usually motivated by several goals, among which: increasing data resolution in one or several dimensions (e.g., temporal, spatial, spectral or angular), decreasing launch costs, increasing data bandwidths, as well as ensuring data continuity and inter-mission validation and complementarity. Constellations have been proposed in several NASA Decadal Surveys and recent studies; in Earth Science (e.g., a multi-spacecraft Landsat for increasing temporal resolution), in Heliophysics (e.g., the Geospace Dynamics Constellation) or in Planetary Science (e.g., the Lunar Geophysical Network). Many constellations and Formation Flying missions have also been proposed more recently in cubesat-related research projects. For the purpose of this subtopic, we do not assume the spacecraft to be of any specific sizes, i.e., we do not restrict this study to cubesats or smallsats. 

The goal of this subtopic is to mature NASA capabilities to formulate and implement novel science missions based on distributed platforms. Technologies solicited in this call are the following: 

• Novel DSM-enabling technologies such as:
• Technologies for high-bandwidth and efficient inter-satellite communication.
• Metrology systems capable of sensing and controlling relative position and/or orientation of multi-element DSMs to sub-milli-arcsecond angular resolution and sub-micro-meter positional accuracy.
• Autonomous and scalable ground-based constellation operations approaches including science operations and data management, and compatible with the Goddard Mission Services Evolution Center (GMSEC) (open source software developed at NASA Goddard).
• Scalable DSM flight software systems such as:
• Software components compatible with the Core Flight System (CFS) (open source software developed at NASA Goddard), enabling to control and navigate DSM formations and constellations; for example, discrete event supervisors offering a means to autonomously control systems based on selected mission metrics (e.g., spacecraft separation distance, number of active spacecraft, etc.).
• Technologies for onboard collaborative processing and intelligence, including but not limited to, inter-spacecraft collaboration for collecting, storing and downloading data as well as multi-platform Science observation coordination and event targeting. 

Research proposed to this subtopic should demonstrate technical feasibility and should discuss how it relates to NASA programs and projects. Proposed work is expected to be at an entry Technology Readiness Level (TRL) between 2 and 5, and to demonstrate a TRL increase of at least one level during each phase of the project. Proposals will be evaluated based on their degree of innovation and their potential for future infusion. 

Future manned space missions will require spacecraft and launch vehicles that are capable of monitoring the structural health of the vehicle and diagnosing and reporting any degradation in vehicle capability.  This subtopic seeks new and innovative technologies in structural health monitoring (SHM) and integrated vehicle health management (IVHM) automated systems and analysis tools.  Techniques sought include modular/low mass-volume systems, low power, low maintenance systems, and complete systems that reduce or eliminate wiring, as well as smart-sensor systems that provide processed data as close to the sensor and systems that are flexible in their applicability.  Examples of possible automated sensor systems are: Surface Acoustic Wave (SAW)-based sensors, passive wireless sensor-tags, flexible sensors for highly curved surfaces, flexible strain and load sensors for softgoods products (broadcloth, webbing or cordage), direct-write film sensors, and others.  Damage detection modes include leak detection, ammonia detection, micrometeoroid impact and others.  Reduction in the complexity of standard wires and connectors and enabling sensing functions in locations not normally accessible is also desirable.  Proposed techniques should be capable of long term service with little or no intervention. Sensor systems should be capable of identifying material state awareness and distinguish aging related phenomena and damage conditions in complex composite and metallic materials.  Techniques and analysis methods related to quantifying material properties, density, microcrack formation, fiber buckling and breakage, etc. in complex composite, metallic and softgoods material systems, adhesively bonded/built-up and/or polymer-matrix composite sandwich structures are of particular interest.  Some consideration will be given to the IVHM /SHM ability to survive in on-orbit and deep space conditions, allow for changes late in the development process and enable on orbit modifications.  System should allow NASA to gain insight into performance and safety of NASA vehicles as well as commercial launchers, vehicles, inflatable structures and payloads supporting NASA missions. Inclusion of a plan for detailed technical operation and deployment is highly favored.

State of the Art 

Current tools for SHM are rudimentary and or need development for future space missions.  Current data analysis methods are frequently non-ideal for the large scales of data needed for SHM analysis and/or require expert involvement in interpretation of data.

This technology enables: 

• Monitoring of advanced structures/vehicles.
• Cost-effective methods for optimizing SHM techniques.
• Feasible methods for validating structural health monitoring systems.

Once developed this technology can be infused in any program requiring advanced structures/vehicles Aerospace companies are very interested in this enabling technology.

STMD/NASA/NARP/National - Directly aligns with NASA space technology roadmaps and Strategic Space Technology Investment plan.

The objective of this subtopic is to develop information technologies that enable robots to better support space exploration. Improving robot information technology (algorithms, avionics, software) is critical to improving the capability, flexibility, and performance of future NASA missions. In particular, the NASA "Robotics and Autonomous Systems" technology roadmap (T04) indicates that extensive and pervasive use of robots can significantly enhance future exploration missions that are progressively longer, complex, and operate with fewer ground control resources.

The performance of space robots is directly linked to the quality and capability of the information technologies that are used to build and operate them. Thus, proposals are sought that address the following technology needs:

• Advanced robot user interfaces that facilitate distributed collaboration, geospatial data visualization, summarization and notification, performance monitoring, and physics-based simulation. The primary objective is to enable more effective and efficient interaction with robots remotely operated with discrete commands or supervisory control. Note: proposals to develop user interfaces for direct teloperation (manual control) are not being solicited and will be considered non-responsive.
• Navigation systems for mobile robot (free-flying and wheeled) operations in man-made (inside the International Space-Station) and unstructured, natural environments (Earth, Moon, Mars). Emphasis on multi-sensor data fusion, obstacle detection, and localization. The primary objective is to radically and significantly increase the performance of mobile robot navigation through new sensors, avionics (including COTS processors for use in space), perception algorithms and software. Proposals for small size, weight, and power (SWAP) systems are particularly encouraged.
• Robot software systems that support system-level autonomy, instrument/sensor targeting, downlink data triage, and activity planning. The primary objective is to facilitate the creation, extensibility and maintenance of complex robot systems for use in the real-world. Proposals that address autonomy for planetary rovers operating in rough terrain or performing non-traditional tasks (e.g., non-prehensile manipulation) are particularly encouraged.

Proposers are encouraged to target the demonstration of these technologies to existing NASA research robots or current projects in order to maximize relevance and potential for infusion.

Deliverables to NASA:

• Identify scenarios, use cases, and requirements.
• Define specifications based on design trades.
• Develop concepts and prototypes.
• Demonstrate and evaluate prototypes in real-world settings.
• Deliver prototypes (hardware and/or software) to NASA.

The use of robotics for In-Situ Resource Utilization (ISRU) in outer space on various planetary bodies is essential since it uses large quantities of regolith that must be acquired and processed. In some cases this will happen while the crew is not there yet, or it will take place at a remote destination where the crew cannot spend much time doing Extra Vehicular Activity (EVA) due to radiation exposure limits.  Large communications latencies mandate autonomous robotics applications. Proposals are sought which provide solutions for the following regolith resources and robotics related technology areas:

Robotic Site Preparation and Construction for Civil Engineering Infrastructure

Future human bases on planetary surfaces, moons and asteroids will require infrastructure to ensure the survival of the crew as well as to prolong the life times of equipment operating in harsh and extreme environments. Since humans will not be at the destination in the early phases of the base construction, robotic equipment that operates autonomously will be required. Civil engineering infrastructure such as landing pads, berms, roads, equipment hangars, dust free zones, thermal wadis, shelters, radiation shielding and habitats will be needed.  Regolith handling systems, fully autonomous site preparation, paver laying robots, inter-locking brick stacking robots, modular structure assembly robots and regolith 3D additive construction systems are encouraged. Proposals are sought for innovative robotic site preparation and construction mission concepts, technology development, and demonstrations. Proposals will be evaluated on the basis of mass, power, volume, feasibility of the concept of operations and complexity. 

Regolith Derived Feed Stocks for In-Situ Robotic Manufacturing

By manufacturing spare parts, structures and surface systems on planetary surfaces, moons and asteroids, large logistics reductions can be achieved by avoiding the transportation of raw materials, commodities and goods from Earth.  The regolith contains many minerals that can be processed to extract resources for manufacturing such as metals, organics, ceramics, glasses and polymers.  In addition, the regolith can be used as a bulk aggregate which can be melted, sintered, or consolidated with a binder material such as in-situ manufactured polymers or other naturally occurring binder materials to form concrete like materials.  Proposals are sought for regolith derived feed stocks that can be used to manufacture spare parts, structures or surface systems. Digital materials and associated regolith derived materials for use in voxel based manufacturing and innovative additive manufacturing methods are also encouraged. Other innovative manufacturing methods such as automated casting, materials deposition or automated assembly methods are also in scope. The emphasis in Phase I shall be on proving that a viable material can be developed with a proof of concept demonstration and related materials properties shall be provided. In Phase II a full scale robotic manufacturing demonstration shall be accomplished which would show how the feedstock could be used to make useful parts, structures or surface systems. Proposals will be evaluated on the basis of material accessibility, economic viability of the ore, feasibility of extraction or processing, materials properties, the concept of manufacturing and applications.

 Proposals are sought for associated innovative resource utilization mission concepts, technology development, and demonstrations but must be based on regolith materials, robotic methods and highly innovative technologies.

NASA's plans to explore space beyond Low Earth Orbit will push the performance of life support systems toward closed loop living systems. Deep space missions will require life support systems that will be self-sustaining since we cannot expect to carry enough spares and consumables for year-long missions. Achieving the development of such systems will provide the understanding for managing the limited availability of resources. The parallel with earth planetary resources management is useful as the world population grows and resources and infrastructure availability decreases. We anticipate that technologies developed for closed loop living systems could be made available to provide near term planetary sustainability as well. 

State of the Art 

An immediate example of such endeavors exists in the form of the NASA Ames Sustainability Base where technologies for deep space exploration have been used to create one of the greenest buildings in the federal building inventory. These technologies include power generation with fuel cells, water recovery systems, advanced HVAC, automated environmental control, recyclable materials and use of local resources. Even though these technologies are readily available for deep space travel, each has its own set of challenges for adaption to earth application along with integration challenges. 

Closed-loop living systems are based on the thermodynamics laws of the conservation of mass and energy. We hope to maximize the conservation so that only a minimal amount of spare resources needs to be taken on crewed deep space missions.

Innovations are sought to enable: 

• Development of processes and technologies to allow for closed loop living applications in space and on earth.
• Transfer of advanced deep space life support technologies and systems to earth based applications.
• Development of viable off-the-gridhabitation in remote areas where infrastructure is inexistent. 

Potential deliverables include a demo of ECLSS concept(s), enhanced process and control techniques for multiple life support subsystems (e.g., environment, water recovery, power usage, etc.), or prototype(s) of relevant hardware and/or software.

For integrated system health management and monitoring capabilities that support sustainable systems, respondents are encouraged to consider SBIR subtopic - H6.01.

In the current design of the Advanced Space Suit, the water necessary to provide cooling to the human and avionics is stored in the Feedwater Supply Assembly (FSA) which resides inside the habitable volume of the Space Suit. The FSA is a flexible reservoir which takes advantage of the suit pressure as the means of maintaining water loop pressure at operation conditions. During the EVA timeline, it is paramount that crew member cooling is uninterrupted. An interruption could cause overheating of the crew member.  Therefore, insight in to the quantity of water remaining is important.

The ability to determine the quantity of a consumable liquid (e.g., water for cooling) remaining in a soft-walled, flexible reservoir via the use of one (ideally) or more sensors presents a difficult challenge for spaceflight applications.  It presents a problem because the reservoir is flexible and it will be in micro-gravity during operation.

Typically, flexible reservoirs in micro-gravity are maintained at a relatively constant external pressure. Therefore, they will collapse as the liquid is consumed from the reservoir.  This occurs as such a low rate, it has presented a challenge for traditional flow rate sensors.  Also, numerous conditions contribute to the challenge.  These challenges include the potential for gas(s) to be entrained in the liquid, the presence or lack of a gravity gradient, and motion of the liquid within the reservoir.  Additionally, the constraints of spaceflight cause even more challenges such as:

• Sensor systems must be optimized for minimal mass, volume, and power consumption.
• They must be highly reliable and require minimal maintenance.
• Must cause minimal hazards to the vehicle, crew, and mission.

The development of human space exploration vehicles and habitats requires an understanding of the relationships and interactions among the technical and human crew aspects of the system. This STTR subtopic seeks to enable creation of modeling and estimation capabilities that will inform system design decisions for enhancing mission success, crew task performance, and crew safety while reducing technical resource demands such as those on mission mass, power, volume and crew time. Currently there is no integrated framework in which to perform system design trades among various vehicle design capabilities taking into account the wide range of roles of the human crewmembers such as mission task performers, vehicle inhabitants, and even medical patients and caregivers. Life support inputs and outputs are accommodated in design considerations; however, this scope provides incomplete coverage of the human interactions with the system design. Just as vehicle and component life-cycle issues must be considered in system design, human adaption throughout a mission in areas such as individual and team behavioral health, physiological performance and clinical health must be folded in to inform vehicle and habitat system design decisions. Innovative approaches to modeling the mutual influences between the technical and human aspects of the exploration system are sought in to inform design trades and prioritization of system technology development. Methods are sought to systematically model and estimate impacts to the behavioral, physiological and clinical outcomes on crewmembers relative to vehicle design options, incorporating how the vehicle and humans will evolve and interact over the course of a mission. It is anticipated these methods will reveal attributes, or groups of attributes, of a system design as influential that would not otherwise be detected in the design phases of mission development. Model validation is not included in this topic call. Methods and demonstrations of application to informing system trade studies and technology development prioritization are included in the scope.

NASA’s future long-duration missions require a high degree of materials recovery and recycling as well as the ability to manufacture required mission resources in-situ. While physico-chemical methods offer potential advantages for the production of many products, biological systems are able to manufacture a wide range of materials that are not yet possible with abiotic systems.  Microbial systems are currently being developed by academic institutions, industry, and government agencies to produce a wide array of products that are applicable to space missions.  Relevant mission resources include, but are not limited to, food, nutrients, pharmaceuticals, polymers, fuels and various chemicals.

While current space-based research involves engineering of organisms to produce targeted compounds as well as the in-situ production of microbial media to support larger scale operations, additional enabling research is needed to develop specialized bioreactors that are highly efficient, reliable, low volume and mass, and that otherwise meet the unique rigors of space.

Advanced bioreactor research and development has been primarily focused on terrestrial applications, particularly pharmaceutical, food and chemical production systems. Some space bioreactor work regarding flight experiments and life support applications has been conducted, such as algal reactors for CO₂/O₂ management.  However, little to no effort has been conducted on the bioreactor design and operations that are required to enable in-situ microbial manufacturing. Therefore, innovations are sought to provide:

• Bioreactors that minimize mass, power and volume, maintenance, process inputs and waste production.
• Bioreactors that are capable of operating in the space environment, including reduced gravity.
• Bioreactors that incorporate novel microbial biomass separation/harvesting/purification methods, and materials recycling/recovery.
• High-density bioreactors that are capable of producing extremely high levels of microbial biomass and/or product.
• Advanced bioreactor monitoring and control systems, including oxygen, temperature, pH, nutrients.
• Experimental bioreactors that exhibit the ability to scale upwards.
• Bioreactors that maximize reliability, component miniaturization, materials handling ability, gas management and overall performance.

The Phase I STTR deliverable should include a Final Report that captures any scientific results and processes as well as details on the technology identified. The Final Report should also include a Feasibility Study which defines the current technology readiness level and proposes the maturation path for further evolution of the system.  Opportunities for commercial and government infusion should be addressed. Other potential deliverables include bioreactor system designs, hardware components and prototypes, and system control approaches and software.

Producing food for crew consumption is an important goal for achieving Earth independence and reducing the logistics associated with future exploration missions.  NASA seeks innovative technologies to enable plant growth systems for food production for in-space and planetary exploration missions.     

Nutrient Recycling

NASA seeks technologies that would enable generation and use of essential nutrients for plant growth (P, N, K) that would otherwise have to be provided by time release fertilizers shipped from Earth.  Separation of targeted useful nutrients or sequestration of sodium from solution to leave useful nutrients are both desired.  Sources of nutrients could include urine, urine that has been pretreated with strong acids or oxidizers, waste biomass from the inedible portions of plants, other spacecraft wastes, or possibly planetary surface regolith.

Cultivation and Growth Systems

Spacecraft systems are constrained to utilize minimal volume and require minimal crew time for management and operation.  NASA seeks innovative systems for plant growth and cultivation that are volume efficient, flexible for a range of plant types and sizes (examples: tomatoes, wheat, beans, potatoes), are adaptive for the entire life cycle (from anchoring the seed, managing the plant growth from seedling through harvest), and is reusable across multiple harvests.  Concepts need to address integration with watering and nutrient/fertilizer systems (whether soil/media based, hydroponic, or aeroponic).  Systems should address whether they are microgravity compatible, surface gravity compatible, or both.

Greenhouse Films

NASA seeks new materials that are flexible, transparent to light used by plants, and survive pressurization.  They need to survive the challenges of a Mars surface environment, such as UV, temperature extremes, and exterior particulate and dust damage and accumulation.

This subtopic is focused on developing and demonstrating technologies for both orbital and in-situ compositional analysis and mapping that can be proposed to future planetary missions. Technologies that can increase instrument resolution, precision and sensitivity or achieve new and innovative scientific measurements are solicited. For example missions, see (http://science.hq.nasa.gov/missions). For details of the specific requirements see the National Research Councils, Vision and Voyages for Planetary Science in the Decade 2013-2022 (http://solarsystem.nasa.gov/2013decadal/).

Possible areas of interest include:

• Improved sources such as lasers, LEDs, X-ray tubes, etc. for imaging and spectroscopy instruments (including Laser Induced Breakdown Spectroscopy, Raman Spectroscopy, Deep UV Raman and Fluorescence spectroscopy, Hyperspectral Imaging Spectroscopy, and X-ray Fluorescence Spectroscopy).
• Improved detectors for imaging and spectroscopy instruments (e.g., flight-compatible iCCDS and other time-gated detectors that provide gain, robot arm compatible PMT arrays and other detectors requiring high voltage operation, detectors with improved UV and near-to-mid IR performance, near-to-mid IR detectors with reduced cooling requirements).
• Technologies for 1-D and 2-D raster scanning from a robot arm.
• Novel approaches that could help enable in-situ organic compound analysis from a robot arm (e.g., ultra-miniaturized Matrix Assisted Laser Desorption-Ionization Mass Spectrometry).
• "Smart software" for evaluating imaging spectroscopy data sets in real-time on a planetary surface to guide rover targeting, sample selection (for missions involving sample return), and science optimization of data returned to earth.
• Other technologies and approaches (e.g., improved cooling methods) that could lead to lower mass, lower power, and/or improved science return from instruments used to study the elemental, chemical, and mineralogical composition of planetary materials.
• Projects selected under this subtopic should address at least one of the above areas of interest. Multiple-area proposals are encouraged. Proposers should specifically address:
• The suitability of the technology for flight applications, e.g., mass, power, compatibility with expected shock and vibration loads, radiation environment, interplanetary vacuum, etc.
• Relevance of the technology to NASA's planetary exploration science goals.

Phase I contracts will be expected to demonstrate feasibility, and Phase II contracts will be expected to fabricate and complete laboratory testing on an actual instrument/test article.

Integrated photonics generally is the integration of multiple lithographically defined photonic and electronic components and devices (e.g., lasers, detectors, waveguides/passive structures, modulators, electronic control and optical interconnects) on a single platform with nanometer-scale feature sizes.  The development of photonic integrated circuits permits size, weight, power and cost reductions for spacecraft microprocessors, communication buses, processor buses, advanced data processing, and integrated optic science instrument optical systems, subsystems and components. This is particularly critical for small spacecraft platforms. On July 27, 2015 - Vice President Joe Biden, at an event in Rochester, NY, announced the New York consortium has been selected to lead the Integrated Photonics Institute for Manufacturing Innovation. For details see (http://manufacturing.gov/ip-imi.html).  Proposed as part of President Obamas National Network for Manufacturing Innovation (NNMI), the IP-IMI was established to bring government, industry and academia together to advance state-of-the-art photonics technology and better position the United States relative to global competition in this critical field.  The use of the IP-IMI for work proposed under this topic is highly encouraged.  This topic solicits methods, technology and systems for development and incorporation of active and passive circuit elements for integrated photonic circuits for:

• Integrated photonic sensors (physical, chemical and/or biological) circuits: NASA applications examples include (but are not limited to): Lab-on-a-chip systems for landers, Astronaut health monitoring, Front-end and back-end for remote sensing instruments including trace gas lidars Large telescope spectrometers for exoplanets using photonic lanterns and narrow band filters.  On chip generation and detection of light of appropriate wavelength may not be practical, requiring compact hybrid packaging for providing broadband optical input-output and also, as means to provide coupling of light between the sensor-chip waveguides and samples, unique optical components (e.g.,  Plasmonic waveguides, microfluidic channel) may be beneficial.
• Integrated Photonic Circuits for Analog RF applications: NASA applications include new methods due to Size, Weight and Power improvements, passive and active microwave signal processing, radio astronomy and TeraHertz spectroscopy.  As an example, integrated photonic circuits having very low insertion loss (e.g., ~1dB) and high spur free dynamic range for analog and RF signal processing and transmission which incorporate, for example, monolithic high-Q waveguide microresonantors or Fabry-Perot filters with multi-GHz RF pass bands.   These components should be suitable for designing chip-scale tunable opto-electronic RF oscillator and high precision optical clock modules.
• Integrated photonic circuits for very high speed computing: Advanced computing engines that approach TeraFLOP per second computing power for spacecraft in a fully integrated combined photonic and electronic package.

Rocket propulsion development is enabled by rigorous ground testing in order to mitigate the propulsion system risks that are inherent in spaceflight. Test articles and facilities are highly instrumented to enable a comprehensive analysis of propulsion system performance.  This topic area seeks to develop advanced instrumentation technologies which can be embedded in systems and subsystems.  The goal is to provide a highly flexible instrumentation solution capable of monitoring remote or inaccessible measurement locations.  All this while eliminating cabling and auxiliary power.  It is focused on near-term products that augment and enhance proven, state-of-the-art propulsion test facilities.  Rocket propulsion test facilities within NASA provide excellent test beds for testing and using the innovative technologies discussed above.  The technologies developed would be capable of addressing multiple mission requirements for remote monitoring such as vehicle health monitoring.

Embedded sensor systems have the potential for substantial reduction in time and cost of propulsion systems development, with substantially reduced operational costs and evolutionary improvements in ground, launch and flight system operational robustness.  Sensor systems should provide an advanced diagnostics capability to monitor test facility parameters including simultaneous heat flux, temperature, pressure, strain and near-field acoustics. Applications encompass remote monitoring of vacuum lines, gas leaks and fire; where the use of wireless/self-powered sensors to eliminate power and data wires would be beneficial.

Sensor technologies should be capable of being embedded in structures and systems that are smaller, more energy efficient allowing for more complete and accurate health assessments including structural health monitoring for long-duration missions.  Structural health monitoring is one of the Top 83 Technical Challenges (12.3.5).  Nanotechnology enhanced sensors are desired where applicable to provide a reduction in scale, increase in performance, and reduction of power requirements.  Specific technology needs include the following:

• Sensor systems should have the ability to provide the following functionality:
• Measurement.
• Measure of the quality of the measurement.
• Measure of the “health” of the sensor.
• Sensor systems should enable the ability to detect anomalies, determine causes and effects, predict future anomalies, and provides an integrated awareness of the health of the system to users (operators, customers, management, etc.).
• Sensors are needed with capability to function reliably in extreme environments, including rapidly changing ranges of environmental conditions, such as those experienced in space.  These ranges may be from extremely cold temperatures, such as cryogenic temperatures, to extremely high temperatures, such as those experienced near a rocket engine plume.  Collected data must be time stamped to facilitate analysis with other collected data sets.
• Sensor systems should be self-contained to collect information and relay measurements through various means by a sensor-web approach to provide a self-healing, auto-configuring method of collecting data from multiple sensors, and relaying for integration with other acquired data sets.
• The proposed innovative systems must lead to improved safety and reduced test, and space flight costs by allowing real-time analysis of data, information, and knowledge through efficient interfaces to enable integrated awareness of the system condition by users.
• The system provided must interface with existing data acquisition systems and the software used by such systems.
• The system must provide NIST traceable measurements.
• The system design should consider an ultimate use of Space Flight sensor systems, which could be used for multi-vehicle use.

Biomimicry is the imitation of life, natural systems and life's principles characterized by reduced use of energy, water and raw materials. Energy and material use is minimized through information and structure. The goal of this topic is to focus efforts on system driven technology development that draws from nature to solve technical challenges in aeronautics and space exploration. While most of the areas described here pertain to aeronautics, biological models have multiple applications and cross cutting solutions are also welcomed that apply to space technology. 

Proposals must demonstrate that the proposed technology complies with natural principles, patterns and mechanisms. 

Some resources are provided here: NASA workshop: https://www.grc.nasa.gov/vibe; www.asknature.org;   http://toolbox.biomimicry.org/. 

Technology is sought in the following areas: 

Bio-inspired air breathing propulsion technology to mitigate engine and airframe icing, to reduce fuel burn, noise and emissions (ARMD Strategic Thrust 3) 

Community performance goals for subsonic transports include specific levels of reduction in energy consumption, emissions of nitrogen oxides (NO ), and noise, represented as N+1, N+2, and N+3 performance levels. These goals support reductions in carbon emissions expressed in an IATA resolution that calls for a 1.5% average annual fuel efficiency improvement between 2010 and 2020, carbon neutral growth from 2020 onward, and a reduction of 50% in net emissions by 2050 compared to 2005 levels. 

This subtopic calls for proposals to reduce fuel burn, noise and emissions through bio-inspired propulsion system technology including but not limited to blade design, coatings, combustor lining, fuel injectors. Some areas of interest are: 

• Management of 'leakage' flow (over blade tips and from purge cavities) in engines that becomes increasingly significant as engine core sizes decrease below 2.5lbm/s compressor exit corrected flow.
• Cooling technology for turbines that must withstand 3000° F inlet temperature. More generally, technology that can enable OPRs (Overall Pressure Ratios) higher than 60 are sought with linkages clearly demonstrated.
• Acoustic liners and turbomachinery concepts to reduce engine noise to reach ARMD's targeted 52dB reduction by 2025 (TRL 4-6 in 2025).
• Some common biological models are shark skin, owl wings and nautilus shell. 

• Bio-inspired icephobic materials and structures for aeronautics (ARMD Strategic Thrust 1). ARMD plans for continued research in engine and airframe icing to enable air vehicles to safely fly into various types of icing environments. This research will include validated computational and experimental icing simulations, as well as complementary on-board icing sensing radar to enable avoidance of icing conditions and to facilitate safe operation of current and future air vehicle concepts. Icing mechanisms on airframes and in engines differ significantly from each other. Icing is also dependent on flight speed and atmospheric conditions. Thus, methods used for refrigerators may not be applicable to aeronautics. Proposals sought include materials or structures that delay ice formation relative to state of the art, that are relatively low energy to de-ice and multifunctional de-icing or icephobic systems. Well known biological systems or models should not be proposed unless the technology proposed is using a known biological model in a novel way. Examples of such models include shark skin, lotus leaves, pitcher plants. 

Bio-inspired power generation, energy storage, power management and distribution 

The NRC has identified a NASA Top Technical Challenge as the need to "Increase Available Power". Additionally, a NASA Grand Challenge is "Affordable and Abundant Power" for NASA mission activities. It is essential to be able to harness, store and distribute energy while maintaining minimal system mass and complexity. Biological models such as the oriental hornet or electric eel may be obvious candidates. Methods to improve solar cell efficiency or to create structural solar cells are of interest. Goals of this subtopic overlap with subtopic T3.01 Energy Transformation and Multifunctional Power Dissemination.

Power generation and management systems are also of interest to the growing Hybrid Gas Electric Propulsion Project under ARMD. There is specific interest in motor thermal management and low loss power distribution and storage. New concepts for electric motors and hybrid systems are desirable. 

Cross cutting technology making use of bio-inspired processes in conjunction with 1 or more of big data analytics, synthetic biology and additive manufacturing.  

Specific areas of interest include: 

• Demonstrations of advantages in mass savings made possible through bioinspired topologies enabled by additive manufacturing methods.
• Controlled synthesis of lightweight engineering materials due to bioinspired synthesis methods.

As composite structures become more prevalent on launch vehicles, it will become necessary to have the capability to inspect and repair these structures during ground processing prior to launch. Current composite repair methods developed for the aviation industry are time consuming and require complex infrastructure in order to restore the structural strength. Aerospace structures have structural and thermal profiles which are different than aircraft and require different considerations; for example, unlike a commercial aircraft, a launch vehicle sees high loading but is only a one time use vehicle. Advancements are needed to repair materials and methods which allow for a structural repair to be performed in locations with minimal access and in a short time frame. Small damages may be accepted by analysis with no repair. Large damages may require extensive repair or component replacement. This subtopic focuses on developing novel composite repair methods for damages that fall in between these two categories. These novel materials and methods should consider the following:

• Use of out of autoclave composite materials and processes, which are being investigated for large launch vehicle components, such as fairings, skirts and tanks on the Space Launch System vehicle. Advancements in these material systems has begun to approach properties of autoclave materials but allow for larger structures to be fabricated. 
• Simplified preparation of the damaged structure. Current methods require very precise methods, which is time consuming and can be a risk for further damage.
• Material systems and methods which reduce or eliminate the need for external heat and/or vacuum. These require complex infrastructure, which can be difficult to accommodate at the launch pad, and can be time consuming, which could cause a launch delay.
• Ability to acquire data on the state of the repair, during repair and/or during the launch. This may include data such as temperature at the bondline during cure, strain across the repair patch, etc. 

Development of a material system and repair method which increases the performance of the repair and reduces the complexity and time required to perform a repair increases the launch capability and success rate. Improvements or modifications to current materials and processes can be made to meet NASA requirements. This technology can also be expanded to develop methods for in-situ repairs to spacecraft on long missions.

The use of thin-ply composites is one area of composites technology that has not yet been fully explored or exploited by NASA.  Thin-ply composites are those with cured ply thicknesses below 0.0025” and commercially available prepregs are now available with ply thicknesses as thin as 0.00075”.  By comparison, a standard-ply-thickness composite would have a cured ply thickness of approximately 0.0055”.  Thin-ply composites hold the potential for reducing structural mass and increasing performance due to their unique structural characteristics, which include (when compared to standard-ply-thickness composites):

• Improved damage tolerance.
•  Resistance to microcracking (including cryogenic-effects).
• Improved aging and fatigue resistance.
• Reduced minimum-gage thickness.
• Increased scalability.

These characteristics can make thin-ply composites attractive for a number of applications.  For example, preliminary analyses show that the notched strength of a hybrid of thin and standard ply layers can increase the notched tensile strength of laminates by 30%.  The resistance to microcracking makes thin-ply composites an excellent candidate for a deep-space habitation structure where hermeticity is critical.  Additionally, since a deep-space habitat may need to be pre-positioned in space for a long period of time prior to crew arrival, the enhanced aging and fatigue resistance and resistance to cryogenic-induced microcracking will also be a benefit.  Finally, since the designs of these types of pressurized structures are typically constrained by minimum gage considerations, the ability to reduce that minimum gage thickness offers the potential for significant mass reductions.  For these reasons, NASA is interested in exploring the use of thin-ply composites for applications requiring very high structural efficiency, and for pressurized structures (such as habitation systems and tanks) for deep-space exploration systems. There are many needs in development, qualification and deployment of composite structures incorporating thin-ply materials – either alone or as a hybrid system with standard ply composite materials.  The particular capabilities requested for in a Phase I proposal in this subtopic are: initial process development in using thin-ply prepregs for component fabrication using automated tape layup or other robotic technologies, contributing to the development of the design and qualification database though testing and interrogation of the structural response and damage initiation/progression at multiple scales including evaluation of environmental durability and ageing, and/or analysis and design tool validation and calibration to ensure that the technology to appropriately design and certify thin-ply composite components is matured sufficiently to be used for NASA applications.  The intention of a Phase II follow-on effort would be to develop or to further mature the necessary design/analysis codes, and to validate the approach though design, build, and test of an article representative of the component/application of interest to NASA.

Additive manufacturing is becoming a leading method for reducing costs, increasing quality, and shortening schedules for production of innovative parts and component that were previously not possible using more traditional methods of manufacturing. In the past decade, methods such as selective laser melting (SLM) have emerged as the leading paradigm for additive manufacturing (AM) of metallic components, promising very rapid, cost-effective, and on-demand production of monolithic, lightweight, and arbitrarily intricate parts directly from a CAD file. In the push to commercialize the SLM technology, however, the modeling of the AM process and physical properties of the resulting artifact were paid little attention. As a result, commercially available systems are based largely on hand-tuned parameters determined by trial and error for a limited set of metal powders. The system operation is far from optimal or efficient, and the uncertainty in the performance of the produced component is too large. This, in turn, necessitates a long and costly certification process, especially in a highly risk-aware community such as aerospace. Modeling and real time process control of selective laser melting is needed coupled with statistically significant correlations and understanding of the important process parameters and the resultant microstructural and mechanical properties, validated with detailed metallurgical investigations of the as-fabricated structures. 

State-of-the-Art 

This topic seeks technologies that close critical gaps between SOA and needed technology in both experimental and analytical areas in materials design, process modeling and material behavior prediction to reduce time and cost for materials development and process qualification for SLM. 

Technological advancements are needed in the areas of: 

• Real-time additive manufacturing process monitoring for real-time material quality assurance prediction. 
• Reduced-order physics models for individual phases of additive manufacturing technique.
• Analytical tools to understand effects of process variables on materials evolution.
• Digital models to standardize the use of structured light scanning or equivalent within manufacturing processes.
• Software for high-fidelity simulation of various SLM phases for guiding the development, and enabling the subsequent verification.

Launch and landing operations through the atmosphere of a planet are strongly affected by environmental and atmospheric conditions.  Even the most robust vehicle design has physical limits that restricts the conditions through which it can be launched.  Divergent fluid dynamics, lightning, and other severe conditions can overstress vehicle structures and cause a mishap. In addition, the safety of personnel performing launch preparations must be protected from extreme weather such as lightning in a manner that minimizes risk to the launch schedule.  A key metric of launch architecture is the overall system’s launch availability, which is in turn impacted by the accuracy with which the environmental conditions can be characterized.  Advanced technologies are being solicited to improve the accuracy of launch and landing environment forecasting and evaluation.  This technology is of interest not only for earth-based launches, but also to enable routine launch and landing activity on other planets such as Mars, where range infrastructure will be extremely limited.  Specific areas of interest include the following: 

Remote Sensing

During launch preparations, an acceptable launch environment that does not impart vehicle damage during ascent is critical. Currently, launch environment conditions such as wind direction, speed, temperature, humidity, and pressure are measured by launching several balloons with rawinsondes on launch day.  The data is then used to construct a vertical profile initializing meteorological models that derive atmospheric stresses on a launch vehicle.  Current technology is used for remote measurements of wind speed and direction as a function of altitude; however, there is no current capability to measure temperature and humidity as a function of altitude remotely in a cloudy environment.  This capability needs to be satisfied by remote methods in order to improve accuracy by measuring overhead and improving timeliness by reducing the lag time to make the measurement and reducing the interval between measurements.  In addition, a remote sensing approach would enable a lower cost simplified launch environment analysis with less infrastructure by eliminating the need for balloons and rawinsondes.

Technology is being sought which provides a remote sensing capability to measure thermodynamic data with respect to altitude from 300 meters to at least 10 km.  The technology must have a vertical measurement resolution of 150 m or smaller and a full vertical profile of the thermodynamic data at least once an hour.  The sensor must provide valid data in both cloudy and clear environments.  Phase I should include a design for remote measurement of at least temperature and humidity as a function of altitude.  Phase II should be prototype development, testing, and evaluation of the sensing technology in a subtropical environment as well as continued development to measure, or derive all three temperature, humidity, and pressure.  Locally available rawinsonde data should be used to verify system accuracy.

Three-Dimensional Launch Window Modeling

During launch countdown, data from several disparate meteorological systems are used to evaluate environmental hazards such as triggered lightning during vehicle ascent. There are several rules based upon radar data, lightning location, electric field and the presence of clouds. For example, in certain circumstances, the launch vehicle cannot pass through a radar echo greater than 7.5 dBz. NASA is seeking a capability to simultaneously, and in real-time, visualize three-dimensional (3D) atmospheric data, and rocket/vehicle trajectories. The region in which a rocket/vehicle trajectory can safely travel through will be a 3D solid shape based upon the launch trajectory with allowable trajectory variations, and user-determined standoff distance. E.g., for a given rocket with trajectory variations of 4.5 miles and a safety standoff distance of 10 miles, a 3D shape such as a tube would be centered around the nominal trajectory line, and at all locations occupy the space 10 + 4.5 miles along the nominal trajectory. Atmospheric data will include: satellite, radar, and lightning data as well as meteorological model products (i.e., forecasts of radar data). The user must be able to manipulate the display to change orientation, scale and products/layers within the intersecting area. 

At a minimum, the system should be able to identify areas where the trajectory shape intersect or enclose lightning data from 3D lighting data sources, and cloud data as identified by radar and a local Weather Research and Forecasting (WRF) model. Any data used for the technology or verification will be from the meteorological instrumentation used at KSC and owned by the USAF.  Phase I would be development of requirements, proposed capabilities, and demonstration of sample products. Phase II would be development of application to ingest NASA and USAF meteorological data and products, and manipulate the data within the volume of interest.

Distributed Electric Propulsion (DEP) Aircraft employ multiple electric propulsors to achieve unprecedented performances in air vehicles.  The propulsor could be ducted/un-ducted fans, propellers, cross-flow-fans, etc.  Some of the benefits identified using this propulsion system are reductions in fuel burn/energy usage, noise, emissions, and/or field length.  Addressing ARMD’s Strategic Thrust #3 (Ultra-Efficient Commercial Vehicles) and #4 (Transition to Low-Carbon Propulsion), innovative approaches in designing and analyzing the DEP aircraft are investigated and encouraged.  In support of these two Strategic Thrusts, the following DEP aircraft research areas are to be considered under this solicitation. 

• Explore Subsonic Fixed Wing Aircraft Concepts with the DEP System - Vehicle classes are to be from small on-demand aircraft to large subsonic transport aircraft.  The study shall include vehicle system level assessment including feasibility, design, and benefits assessment.
• Develop Analytical Tools and Methods to Assess DEP Aircraft Concepts – Assessing a feasibility of vehicle concept requires reliable analytical, computational, experimental, and/or simulation tools and methods.  Since the DEP aircraft involve multi-disciplinary subjects, some form of optimization process will be preferred and needed.
• Assess Propulsion Airframe Integration (PAI) Benefits – Synergistic benefit assessment capability needs to be established for aircraft with the DEP system.  Some of the PAI examples include boundary layer ingestion (BLI), aero-propulsive acoustics, induced drag reduction using wing-tip propulsor, use of DEP coupled aeroelasticity effects to improve vehicle performance, etc.
• Develop Aircraft Control Concept using DEP – Aircraft control using differential and/or thrust vectoring of distributed electric propulsors shall be explored.  This may allow reduction or elimination of conventional aerodynamic control surfaces.  

Expected outcome (TRL 2-3) of Phase I awards, but not limited to: 

• DEP aircraft concept definition and system level assessment.
• Initial development of analytical/computational/experimental/simulation tools and methods in assessing DEP concepts and aircraft. 

Expected outcome (TRL 4-6) of Phase II awards, but not limited to: 

• Detailed feasibility study and demonstration of the subscale hardware.
• Refinement of tools and methods in assessing DEP concepts and aircraft.
• Experimental (e.g., wind tunnel) results that assess the validity of the DEP/aircraft concept.

This subtopic is focused on developing and demonstrating technologies for coordination and autonomous control of teams and swarms of space systems including but not limited to spacecraft and planetary rover teams in a dynamic environment. 

Possible areas of interest include but are not limited to: 

• Coordinated task planning, operation, and execution.
• Relative localization in space and on planet surface.
• Close proximity operations of spacecraft swarms including sensors required for collision detection and avoidance.
• Fast, real-time, coordinated motion planning in areas densely crowded by other agents.
• Human-Swarm interaction interfaces for controlling the multi-agent system as an ensemble.
• Distributed fault detection and mitigation due to hardware failures or compromised systems.
• Communication-less coordination by observing and estimating the actions of other agents in the multi-agent system. 

Phase I awards will be expected to develop theoretical frameworks, algorithms, software simulation and demonstrate feasibility (TRL 2-3). Phase II awards will be expected to demonstrate capability on a hardware testbed (TRL 4-6).