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Low Earth Orbit Spacecraft Charging Design Standard

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4000 - Electrical and Electronics Systems, Avionics/Control Systems, Optics
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This standard provides requirements relative to various plasma interactions that can result when a high-voltage system is operated in the Earth's ionosphere and standard practices to eliminate or mitigate such reactions. The purpose of this standard is to provide a design standard for high-voltage space power systems (> 55 volts) (V))that operate in the plasma environment associated with LEO (altitude from 200 and 1000 km and latitude between -50 and +50 degrees). Such power systems, particularly solar arrays, are the proximate cause of spacecraft charging in LEO; and these systems can interact with this environment in a number of ways that are potentially destructive to themselves as well as to the platform or vehicle that has deployed them.
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nasa-std-4005.pdf (180.85 KB)
NASA-STD-4005A.pdf (135.08 KB)
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