As reported previously military space power requirements in the next ten years are 5 to 30 kW steady state. Because of limitations in the capability to deliver satellites to orbit, size and weight of the solar array continue to be important. We also need the capability to operate throughout all orbital regimes from low orbit equatorial and polar to mid altitude (5600 NM) and elliptical as well as the geosynchronous orbits. Each of these orbital regimes have their own set of constraints either weight or environment which must be addressed in the high power solar array technology. High altitude systems are severely weight limited and in addition spacecraft charging must be considered. The low altitude orbits will encounter the plasma environments which may cause severe leakage currents especially at higher operating voltages. The mid altitude orbits encounter severe radiation environments as well as possible spacecraft charging. Also as the voltages increase corona effects may be manifest as a result of outgassing environments internal to the spacecraft. These areas are discussed in the conference paper.
Solar power requirements for military space vehicles
Anforderungen an die Solarzellenbatterien von militaerischen Raumfahrzeugen
1984
6 Seiten, 6 Bilder, 3 Tabellen, 7 Quellen
Aufsatz (Konferenz)
Englisch
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