NASA STTR 2016 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 16-2 T1.01-9785
PHASE 1 CONTRACT NUMBER: NNX16CD17P
RESEARCH SUBTOPIC TITLE: Affordable Nano/Micro Launch Propulsion Stages
PROPOSAL TITLE: Low-Cost, Scalable, Hybrid Launch Propulsion Technology

SMALL BUSINESS CONCERN (SBC): RESEARCH INSTITUTION (RI):
NAME: Physical Sciences, Inc. NAME: Purdue University
STREET: 20 New England Business Center STREET: 155 S. Grant Street
CITY: Andover CITY: West Lafayette
STATE/ZIP: MA  01810 - 1077 STATE/ZIP: IN  47908 - 2114
PHONE: (978) 689-0003 PHONE: (765) 494-6204

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Prakash B. Joshi
joshi@psicorp.com
20 New England Business Center
Andover, MA 01810 - 1077
(978) 738-8202

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. B. David Green
green@psicorp.com
20 New England Business Center
Andover, MA 01810 - 1077
(978) 689-0003 Extension :8146

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

Technology Available (TAV) Subtopics
Affordable Nano/Micro Launch Propulsion Stages is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

Physical Sciences Inc. (PSI), in collaboration Purdue University, proposes to develop a novel launch propulsion technology for rapid insertion of nano/micro satellites (~ 5-100 kg scale) into low earth orbit, with the potential to lower the current state-of-the-art launch stage cost by 2X. The technology employs a propulsion scheme comprising a storable liquid oxidizer and a unique solid fuel with excellent mechanical and thermochemical properties. The proposed application to launch vehicle stages will result in low-cost, mass-efficient launch systems and will reduce technical development risk for NASA. The fuel and oxidizer are commercially available at low cost as an inexpensive engineering material and as an industrial chemical. Both have high density, are green, and the system has a high specific impulse (> 275s; vacuum). The oxidizer storage, handling, transportation, and loading operations are simpler and safer compared to cryogenic/toxic propellants. The foregoing  attributes enable the lower cost of the proposed hybrid launch vehicle stage. The performance of current hybrids is limited by their typically low fuel regression rates. In Phase I, we investigated techniques for significantly augmenting the regression rate, demonstrating ~ 3.5X increase in 30 lbf thruster firings. Using this data, we performed design trades for a hybrid stage as the second/upper launch vehicle stage. The enhanced regression rate allowed a more compact, lighter, higher thrust-to-weight stage than would be possible with current hybrids. In Phase II, we will perform detailed experiments to optimize propulsive performance on the same Phase I hybrid thruster, and demonstrate a large scale (~1000 lbf) motor, representative of upper stages of a launch vehicle incorporating the optimized design. Phase II will end with a flight prototype design and a plan for a sub-orbital flight test, or a comprehensive ground test in simulated environment.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The NASA application for the proposed launch vehicle stage technology is for insertion of nano/micro satellites into LEO over a range of inclinations. Initial applications are likely to be upper stages of launch vehicles. However, the technology can also be applied to other stages and to in-space propulsion, where high thrust at moderate impulse is required. The superior thermomechanical properties of our fuel are attractive for lighter propulsion systems as structural containment requirements are lowered and additional liner/insulation materials are unnecessary.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The non-NASA applications for the proposed launch vehicle stage technology include Air Force, Navy, and National Reconnaissance Organization missions to insert nano satellites into LEO over a range of inclinations and to in-space propulsion, where high thrust at moderate impulse is required. The commercial sector and educational institutions would also benefit from a substantially lower cost access to low earth orbit. The superior thermomechanical properties of the fuel will produce lighter propulsion systems for all applications.

TECHNOLOGY TAXONOMY MAPPING (NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.)
Fuels/Propellants
Launch Engine/Booster

Form Generated on 07-27-17 15:53