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Performance characterization and transient investigation of multipropellant resistojetsThe multipropellant resistojet thruster design initially was characterized for performance in a vacuum tank using argon, carbon dioxide, nitrogen, and hydrogen, with gas inlet pressures ranging from 13.7 to 310 kPa (2 to 45 psia) over a heat exchanger temperature range of ambient to 1200 C (2200 F). Specific impulse, the measure of performance, had values ranging from 120 to 600 seconds for argon and hydrogen respectively, with a constant heat exchanger temperature of 1200 C (2200 F). When operated under ambient conditions typical specific impulse values obtained for argon and hydrogen ranged from 55 to 290 seconds, respectively. Performance measured with several mixtures of argon and nitrogen showed no significant deviation from predictions obtained by directly weighting the argon and nitrogen individual performance results. Another aspect of the program investigating transient behavior, showed responses depended heavily on the start-up scenario used. Steady state heater temperatures were achieved in 20 to 75 minutes for argon, and in 10 to 90 minutes for hydrogen. Steady state specific impulses were achieved in 25 to 60, and 20 to 60 minutes respectively.
Document ID
19890015912
Document Type
Technical Memorandum (TM)
Authors
Braunscheidel, Edward P. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1989
Subject Category
SPACECRAFT PROPULSION AND POWER
Report/Patent Number
NAS 1.15:102118
E-4897
NASA-TM-102118
AIAA PAPER 89-2837
Meeting Information
Joint Propulsion Conference(Monterey, CA)
Funding Number(s)
PROJECT: RTOP 474-52-10
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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