The Space Shuttle Orbiter has the geometrical configuration of an aircraft and nonconducting outer skin that is expected to generate considerable transient charging and local potential differences due to the ambient ionospheric plasma. Emission of high-current electron beams has been proposed for the AMPS Spacelab payload that would induce large potentials and return currents to the orbiter skin. Quantitative estimates are presented for the magnitude and transient behavior for both the passive and active conditions.
Electrical charging of Shuttle Orbiter
Elektrische Aufladung des Raumfahrzeuges Shuttle Orbiter
IEEE Transactions on Plasma Science ; PS-4 , 4 ; 229-240
1976
12 Seiten, 16 Quellen
Aufsatz (Zeitschrift)
Englisch
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