SBIR/STTR
On-Board Pressurization Systems for Sample Return Missions, Phase I
Project Introduction
To-date, the realization of high-performance liquid bipropellant rocket engines for ascent vehicle and sample return applications has largely been hindered by the inability to obtain "on-board" pressurization through a light-weight and low-complexity pump. Ventions seeks to fulfill this critical need by designing, fabricating and testing an electric pump for a Mars Ascent Vehicle compatible with LOX / propane produced via in-situ resource utilization to achieve significant performance improvements over the current baseline.
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Anticipated Benefits
Potential NASA Commercial Applications: While the proposed pump-fed propulsion system has direct applications for Mars Ascent Vehicles and sample return missions, the enabling technology proposed herein overcomes a key challenge of providing on-board pressurization at the small-scale, thereby enabling a new generation liquid bipropellant rocket engines in the 100-5,000lbf thrust class, with a T/W ratio in excess of 100, and a vacuum Isp >300sec. Other NASA applications for such high-performance propulsion systems are therefore also likely to include lunar ascent / descent missions (precursor rovers, cargo, etc.), Near-Earth-Object (NEO) missions and outer planet orbit capture and insertion.
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Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
Jet Propulsion Laboratory
(JPL)
|
Lead Organization | NASA Center | Pasadena, CA |
| Ventions, LLC | Supporting Organization | Industry | San Francisco, CA |
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Organizational Responsibility
Responsible Mission Directorate:
- Space Technology Mission Directorate (STMD)
Lead Center / Facility:
- Jet Propulsion Laboratory (JPL)
Responsible Program:
- SBIR/STTR
Project Management
Program Director:
Program Manager:
Project Manager:
Principal Investigator:
- Adam P London
Project Duration
Start: Jun 2014
End: Dec 2014
Technology Maturity (TRL)
| Start: | 3 |
| Current: | 4 |
| Estimated End: | 4 |
Applied Research
Development
Demo & Test
Technology Areas
Primary:
- TA 2 In-Space Propulsion Technologies
- TA 2.1 Chemical Propulsion
- TA 2.1.1 Liquid Storable
Other / Cross-cutting:
- TA 2 In-Space Propulsion Technologies
- TA 2.1 Chemical Propulsion
- TA 2.1.2 Liquid Cryogenic
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