Small Business Innovation Research/Small Business Tech Transfer
NOFB-Aerospike
Project Description
We propose the research, development and testing of a clustered aerospike engine to eventually be utilized with our high performance NOFB (nitrous oxide fuel blend) monopropellant and combustion chamber designs (patents pending) for planetary ascent stages. Compared to existing systems, this monopropulsion system concept: 1) achieves bipropellant rocket performance in a compact, monopropellant system architecture; 2) is non-toxic to allow a low cost, extensive engine testing prior to actual flight compared to toxic propellant alternatives; 3) is stable and storable over a very wide range of temperatures and environmental conditions; 4) is <30% of the overall length of an equivalent conventional bell nozzle engine, ~90% of the diameter, and allows high density packaging of mono/bipropellant systems into compact launch configurations reducing propulsion system volume and mass; 5) can be thrust-vectored to remove a separate engine gimbal requirement; and 6) utilizes an atmosphere-compensating nozzle allowing for significant mass savings and consistent performance over a wide range of altitudes.
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Anticipated Benefits
The packaging of a high performance engine into a small volume could readily be used for both DOD and commercial satellite use. Variable orbits used in DOD satellites could benefit from reduced volume thrusters with high thrust output. Additionally GEO communication satellites could readily use this technology as for orbit transfer burns.
The development of a high performance monopropellant aerospike engine has the advantage of compact storage, elimination of a mechanical gimble, and increased reliability due to clustering of more reliable commercial combustion chambers. These attributes are very desirable for single stage to orbit ascent engines and second/third stage engines (to package into tight volumes associated with staging). We believe this solution to be tailorable to the thrust of a mission based on clustering a number of commercial thrusters. More »
The development of a high performance monopropellant aerospike engine has the advantage of compact storage, elimination of a mechanical gimble, and increased reliability due to clustering of more reliable commercial combustion chambers. These attributes are very desirable for single stage to orbit ascent engines and second/third stage engines (to package into tight volumes associated with staging). We believe this solution to be tailorable to the thrust of a mission based on clustering a number of commercial thrusters. More »
Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
| Firestar Engineering, LLC | Lead Organization | Industry | Mojave, California |
Armstrong Flight Research Center
(AFRC)
|
Supporting Organization | NASA Center | Edwards, California |
Primary U.S. Work Locations
-
California
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This is a historic project that was completed before the creation of TechPort on October 1, 2012. Available data has been included. This record may contain less data than currently active projects.