Effect of Solar Illumination on Esd for Structure Used in Spacecraft

Abstract

Abstract-This paper presents the effect of solar illumination on the differential potential generated on the surfaces of spacecraft body in space. Two geometrical cases are considered: 1) Cylindrical symmetry and 2) Tilted metallic plates forming an angle with the adjacent side. The capacitance required for estimation of the body potential is computed by Method of Moment. Nonuniform triangular meshing is used for both the geometrical structures. The differential potential generated on surfaces of a geometrical body due to photoelectric effect results in electrostatic discharge. In the case of the tilted plates, the differential potential at various tilt-angles is computed along with the capacitance computation. In the case of the cylindrical object, the estimation of potential at the day-night interface is shown. The variation in the potential for different incident angles of the solar photons and the changing (h/r) ratio is analyzed. The validity of the analysis is established with that obtained in open literature.

A comparative study of body potential transient profile of geosynchronous orbit spacecraft in single and double Maxwellian plasma models

“…This in turn can trigger the differential charging and make the situation favorable for ESD 4 . Since the initial stage of absolute charging may progress towards its subsequent undesirable stage of differential charging because of dissimilar induced electron yields and different sunlight conditions on the surfaces of a spacecraft, 1–5 a reliable estimation of absolute charging is critically essential. It also demands accurate estimation of the transient profile of the body potential of the fully conductive spacecraft 6,7 …”

Impact of secondary and backscattered electron currents on absolute charging of structures used in spacecraft

“…Charging to high absolute voltages is detrimental as it can influence the instrument functions and scientific experiments as well as the onboard power system. Most prominently, the surface charging may develop into its subsequent stage of differential charging from its initial stage of absolute charging because of dissimilar induced electron yields and different sunlit conditions on the surfaces of a spacecraft . Since differential charging can result in hazardous ESD, the reliable estimation of absolute charging is critically important.…”