Open AccessPerformance of a miniaturized arcjet
Author(s) -
John M. Sankovic,
David Jacobson
Publication year - 1995
Publication title -
31st joint propulsion conference and exhibit
Language(s) - English
Resource type - Conference proceedings
DOI - 10.2514/6.1995-2822
Subject(s) - arcjet rocket , specific impulse , propellant , impulse (physics) , ammonia , materials science , mass flow rate , hydrazine (antidepressant) , limiting , nitrogen , anode , breadboard , chemistry , thermodynamics , aerospace engineering , mechanical engineering , electrical engineering , electrode , engineering , physics , organic chemistry , chromatography , quantum mechanics
Performance measurements were obtained and life-limiting mechanisms were identified on a laboratory-model arcjet thruster designed to operate at a nominal power level of 300 W. The design employed a supersonic-arc-attachment concept and was operated from 200 to 400 W on hydrogen/nitrogen mixtures in ratios simulating fully decomposed hydrazine and ammonia. Power was provided by breadboard power processor. Performance was found to be a strong function of propellant flow rate. Anode losses were essentially constant for the range of mass flow rates tested. It is believed that the performance is dominated by viscous effects. Significantly improved performance was noted with simulated ammonia operation. At 300 W the specific impulse on simulated ammonia was 410 s with an efficiency of 0.34, while simulated hydrazine provided 370 s specific impulse at an efficiency of 0.27.
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