NON-TOXIC MONOPROPELLANTS HAVE BEEN DEVELOPED THAT PROVIDE BETTER PERFORMANCE THAN TOXIC HYDRAZINE. FORMULA…
Award details are derived from public USAspending.gov records. Not a bid recommendation.
Award details
- Award ID
- NNX11CE41P
- Contractor
- Awarding agency
- National Aeronautics and Space Administration
- Sub-agency / office
- National Aeronautics and Space Administration
- Award amount
- $0
- Period of performance
- Jun 7, 2011 – Aug 17, 2011
- NAICS
- 541712 — Research and Development in the Physical, Engineering, and Life Sciences
- PSC
- PSC AR11
- Place of performance
- AL
Public award description
NON-TOXIC MONOPROPELLANTS HAVE BEEN DEVELOPED THAT PROVIDE BETTER PERFORMANCE THAN TOXIC HYDRAZINE. FORMULATIONS BASED ON HYDROXYLAMMONIUM NITRATE (HAN) HAVE SUPERIOR PERFORMANCE AS COMPARED TO HYDRAZINE WITH ISP (261 SECONDS, 12% GREATER), HIGHER DENSITY AND VOLUMETRIC IMPULSE, LOWER MELTING POINT, AND MUCH LOWER TOXICITY (NO SELF CONTAINED BREATHING APPARATUS REQUIRED). HAN BASED MONOPROPELLANTS REQUIRE HIGHER CHAMBER TEMPERATURES (2083K VS 883K) TO COMBUST. CURRENT HYDRAZINE BASED COMBUSTION CHAMBER TECHNOLOGY (INCONEL OR NIOBIUM C103 AND SILICIDE COATING) AND CATALYST (SHELL 405) ARE INADEQUATE. HOWEVER, CURRENT STATE OF THE ART IRIDIUM LINED RHENIUM CHAMBERS ARE COMPATIBLE WITH MONOPROPELLANTS AND NEW IGNITION TECHNIQUES ARE BEING DEVELOPED. THE GOAL OF THE SBIR PROJECT IS FABRICATE AND TEST A FLIGHT WEIGHT THRUST CHAMBER FOR HAN BASED MONOPROPELLANTS.
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