Earth-orbit transfer missions, station keeping, and elusive maneuvering benefit from the application of efficient electric propulsion (EP) systems, The Dual Mode of using significant on-board power (i.e., greater than 10 kW) for the main mission coupled to EP for orbit transfer and maneuvering is creating EP opportunities. Hydrogen arcjets at 1400 s rather than the higher specific impulse ion engines are suitable for SDIO orbit transfer missions; the ion engine's low thrust density and expensive fuels work against it. In 1989, research was initiated on hydrogen arcjets (20 to 50 kW, 1000 to 2000 s specific impulse). Research is being conducted to increase the power and thrust density of ion propulsion (10 to 25 kW, 3500 to 4500 s). Space experiments to gain operational experience are being planned around state-of-the-art ammonia arcjets. Research from 1986 to 1989 focused on the ammonia arcjet for the SP-100 flight mission. The thirty kW arcjet's sustained life and inherent simplicity offer low risk and minimum cost for the SP100 flight demonstration objectives. Solar power flight experiments offer near term opportunities for acquiring flying experience on these nearly developed high power arcjet systems. In addition, lower power (approximately 100 W) engines, can meet drag make-up requirements for small, low orbit space systems.
SDIO Electric Propulsion Requirements
1990
7 pages
Report
No indication
English
Electric & Ion Propulsion , Aerospace systems , Earth orbits , Electric propulsion , Ion propulsion , Missile defense , Propulsion system configurations , Propulsion system performance , Space weapons , Spacecraft maneuvers , Ammonia , Cost effectiveness , Drag , Flight tests , Hydrogen , Ion engines , Low cost , Low thrust , Risk , Space power reactors , Spaceborne experiments , Specific impulse , Stationkeeping
SDIO ELECTRIC PROPULSION REQUIREMENTS
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