SBIR/STTR
"Bantam Rocket Affordable SLV Stage (BRASS)", Phase I
Project Introduction
During the proposed Phase I research and development effort, the project team will integrate previously demonstrated technologies into a stage 4 propulsion system for an existing Small Launch Vehicle (SLV). The resulting fourth stage will meet launch vehicle requirements for Mass Fraction and Specific Impulse. Key stage component will be fabricated and demonstrated. The propulsion system will be evaluated in a hot-fire test series. The proposed project team will develop a plan for a potential follow-on Phase II flight demonstration program.
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Anticipated Benefits
Upper stage propulsion systems for Small/Nano/Micro Launch Vehicles. Satellite propulsion systems.
Upper stage propulsion systems for Small/Nano/Micro Launch Vehicles. Satellite propulsion systems. Ballistic missile Post-Boost Propulsion Systems. Tactical missiles. More »
Upper stage propulsion systems for Small/Nano/Micro Launch Vehicles. Satellite propulsion systems. Ballistic missile Post-Boost Propulsion Systems. Tactical missiles. More »
Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
Armstrong Flight Research Center
(AFRC)
|
Lead Organization | NASA Center | Edwards, CA |
| Exquadrum, Inc. | Supporting Organization | Industry | Adelanto, CA |
| University of Arizona, Tucson | Supporting Organization | Academic | Tucson, AZ |
Primary U.S. Work Locations
-
Arizona
-
California
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Organizational Responsibility
Responsible Mission Directorate:
- Space Technology Mission Directorate (STMD)
Lead Center / Facility:
- Armstrong Flight Research Center (AFRC)
Responsible Program:
- SBIR/STTR
Project Management
Program Director:
Program Manager:
Principal Investigator:
- Marlow Moser
Project Duration
Start: Jun 2017
End: Jun 2018
Technology Maturity (TRL)
| Start: | 5 |
| Current: | 5 |
| Estimated End: | 6 |
Applied Research
Development
Demo & Test
Technology Areas
Primary:
- TA 1 Launch Propulsion Systems
- TA 1.1 Solid Rocket Propulsion Systems
- TA 1.1.4 Hybrid Rocket Propulsion Systems
Target Destination
Earth