LEO orbits may be considered to extend up to 1500 km and can have any orbital inclination. Requirements associated with the following are intended to be adopted by all LEO spacecraft with exposed high voltage systems, e.g. high voltage solar arrays:
• High voltage interactions (clause 8).
• Solar array ESD effects on the array itself (clause 7).
In LEO orbits, unless the spacecraft has electric field sensitive instruments, requirements need not be considered specifically directed at internal parts and materials (clause 6).