Environmental space plasma interactions with spacecraft systems are known to result in corona and arc breakdown induced electromagnetic interference (EMI) generation resulting in spacecraft operational and functional anomalies. The current design of solar array powersources for spacecraft provides for the partial mitigation of the effects of environmental particle interactions in the area of solarcell degradation primarily by the use of solar cell cover glass. Recent findings have indicated the existence of an 'enhanced electron emission' environmental interaction mechanism at low voltage (less than 1 kV) for a negative metal/positive dielectric interface typified by current solar array configurations designed with dielectric cover glass material adjacent to metallic interconnects. Another plasma interaction mechanism of concern is a positive metal/negative dielectric interface, or the 'pin-hole' effect in which collection of secondary electrons by the positively charged metal interconnect from the adjacent dielectrics create a charge differential. This paper surveys the current understanding of environmental plasma induced spacecraft power loss mechanisms and presents design techniques for mitigation of the induced effects.
Environmental plasma interaction considerations in spacecraft power source design
Ueberlegungen zu den Auswirkungen des Raumplasmas fuer die Planung von Raumfahrzeugenergieversorgungssystemen
1984
4 Seiten, 5 Bilder, 5 Quellen
Aufsatz (Konferenz)
Englisch
Environmental Interaction with Spacecraft
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