THE PERFORMANCE LIQUID PROPELLANT ENGINES CAN BE SIGNIFICANTLY IMPROVED BY INCREASING BOTH COMBUSTION TEMPE…
Award details are derived from public USAspending.gov records. Not a bid recommendation.
Award details
- Award ID
- NNX10CF23P
- Contractor
- Awarding agency
- National Aeronautics and Space Administration
- Sub-agency / office
- National Aeronautics and Space Administration
- Award amount
- $0
- Period of performance
- Jan 29, 2010 – Jul 29, 2010
- NAICS
- 541712 — Research and Development in the Physical, Engineering, and Life Sciences
- PSC
- PSC AR11
- Place of performance
- AL
Public award description
THE PERFORMANCE LIQUID PROPELLANT ENGINES CAN BE SIGNIFICANTLY IMPROVED BY INCREASING BOTH COMBUSTION TEMPERATURE AND PRESSURE AND REDUCING ENGINE WEIGHT. STATE OF THE ART BI-PROPELLANT ENGINES ARE METALLIC; THE HIGHEST TEMPERATURE COMBUSTION CHAMBERS ARE MADE OF IRIDIUM/RHENIUM METALS. UTILIZING CARBON-CARBON COMPOSITES FOR THRUST CHAMBER STRUCTURES CAN REDUCE COMPONENT WEIGHT BY AS MUCH AS 90%. UNFORTUNATELY CARBON COMPOSITES SUFFER FROM UNACCEPTABLY HIGH OXIDATION RATES. LINING CARBON-CARBON CHAMBERS WITH A THIN LAYER OF IRIDIUM OR IRIDIUM/RHENIUM IS AN INNOVATIVE WAY TO PROVIDE THE OXIDATION BARRIER NECESSARY TO ENABLE THE USE OF CARBON-CARBON COMPOSITES. THIS PROPOSAL EVALUATES USING METAL-LINED CARBON-CARBON TO PRODUCE HIGH PRESSURE, LIGHT WEIGHT THRUST CHAMBERS.
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