Abstract: A spacecraft includes a spacecraft base structure having an externally facing, electrically conducting spacecraft surface, with the spacecraft structure including a solar cell array. A grounding structure has an externally facing, electrically conducting plasma grounding surface, and an electrical ground extends between the plasma grounding surface and the spacecraft base structure. In space, the spacecraft is oriented with the plasma grounding surface facing the sun. Electron photoemission from the plasma grounding surface balances electron charging of that portion of the spacecraft surface that does not face the sun, preventing electrical charging of the spacecraft relative to the plasma environment.

Abstract: Device and method of protecting a satellite from undesired electrical disturbances without significantly increasing the satellite's weight. The device includes two faraday cage structures around the electronic units of the satellite. The two structures are electrically connected via shielded wires to create one continuous faraday cage. Signals from components located outside the faraday cage to the electronic units are made through filter assemblies. The filter assemblies electronically filter undesired signals before routing desired signals to their destination.