We have developed a Magneto Plasma Dynamic (MPD) thruster system, which was launched on board the test satellite 'TANSEI IV' by the Institute of Space and Aeronautical Science, University of Tokyo on February 17, 1980. The propulsion system consisted of two MPD thrusters and a Data and Control Interface Unit (DCIU). Each thruster was composed of an MPD-Head, Fast Acting Valve (FAV), an Ammonia Propellant Feed System, a Capacitor Bank, and a Charger Unit (CU). The repetition cycle of the thruster operation was limited by the power, 30 W, allocated to the thruster system. The thruster firing was repeated every 32 s. The mass of the entire thruster system was 13,5 kg. MPD thrusters were intermittently operated from March 24 through 26, 1980. The MPD thruster system was operated for 5,6 hours in total. The results of the MPD thruster test in space were satisfactory with respect to the following items: Intermittent operation: On-Off cycle test. Impulse bit measurement by means of satellite spin rate variation: impulse bit of thruster No. 2 was 0,4 Nxms. Propellant phase change in the storage and feed system under near zero gravity conditions. (Wassmann)
Development and flight performance test of MPD thruster system
Entwicklung und Flugerprobung des MPD-Antriebssystems
Ishikawajima-Harima Engineering Review ; 20 , 6 ; 428-436
1980
9 Seiten, 19 Bilder, 2 Tabellen, 15 Quellen
Article (Journal)
Japanese
Flight performance test of MPD thruster system
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