a. It shall be demonstrated that that no self-sustained discharge can occur in any on-board equipment.
NOTE This is generally achieved by insulating high voltage parts.
b. For low Earth orbits when using high voltage solar arrays (above 150 V), it shall be demonstrated that the expected power losses when the solar array is surrounded by a cold and dense plasma is equal or less to a percentage loss agreed with the customer.
NOTE Losses are generally limited to a few percent or less.
c. An analysis shall be performed to determine the potential effect of the grounding of the solar array with respect to the spacecraft on the floating potential of the spacecraft.