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Performance characterization tests of a 1-kW resistojet using hydrogen, nitrogen and ammonia as propellantsA performance mapping test of a 1 kW radiatively heated resistojet demonstrated high specific impulse and efficiency with hydrogen, nitrogen and ammonia as propellants. The resistojet was based on an unmodified augmentation section of the flight-qualified Rocket Research Company Augmented Catalytic Thruster. Peak specific impulse values of 686.9 sec for hydrogen, 191.6 sec for nitrogen, and 342 sec for ammonia were demonstrated. A maximum specific impulse efficiency of 94.3 percent was demonstrated with hydrogen. Testing covered a thrust range of 27 to 112 mlbf with augmentation powers ranging from 300 to 1000 watts. A total of 83 runs accumulating 25 hours of operation were conducted with the three propellants. Comparison of specific impulse efficiency to other published resistojet performance data showed the radiatively heated resistojet compares favorably to other design concepts.
Document ID
19850057477
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Miyake, C. I.
(Rocket Research Corp. Redmond, WA, United States)
Mckevitt, F. X.
(Rocket Research Co. Redmond, WA, United States)
Date Acquired
August 12, 2013
Publication Date
July 1, 1985
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 85-1159
Accession Number
85A39628
Funding Number(s)
CONTRACT_GRANT: NAS3-23868
Distribution Limits
Public
Copyright
Other

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