Passive, elektrische Erdung eines Raumfahrzeuges zu seiner Plasmaumgebung

A spacecraft (20) includes a spacecraft base structure having an externally facing, electrically conducting spacecraft surface (32a), with the spacecraft structure including a solar cell array (26). A grounding structure has an externally facing, electrically conducting plasma grounding surface (44a), and an electrical ground (46) extends between the plasma grounding surface (44a) and the spacecraft base structure. In space, the spacecraft (20) is oriented with the plasma grounding surface (44a) facing the sun. Electron photoemission from the plasma grounding surface (44a) balances electron charging of that portion of the spacecraft surface that does not face the sun, preventing electrical charging the spacecraft (20) relative to the plasma environment.