Qualification and life testing of a flight design hydrazine arcjet systemThis paper describes the design and the requirements of a low-power hydrazine arc jet system and presents the results of tests on the system's performance, vibration, and lifetime. The system consists of an arcjet, catalyst bed, power control unit, and interconnecting power cable. Operating at 1.4 kW input power, the system provides a minimum of 450 sec mission average specific impulse, yielding greater than a 100 kg propellant savings over standard monopropellant or bipropellant systems used on communication satellites.
Document ID
19900055504
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Knowles, S. C. (Rocket Research Corp. Redmond, WA, United States)
Yano, S. E. (Rocket Research Corp. Redmond, WA, United States)
Aadland, R. S. (Rocket Research Co. Redmond, WA, United States)