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- W2037454172 abstract "Thermal considerations require the use of dielectric materials such as Kapton and Teflon on the outside layers of spacecraft. These materials have the right thermo-optical properties (such as absorptance and emittance) and the right mechanical properties (such as tensile strength and density). When subjected to the space environment which prevails in a geostationary orbit, however, these materials charge up to several thousand volts and eventually, when the breakdown potential of the material is reached, they produce a spontaneous discharge with catastrophic effects on the logic circuits aboard the satellite, and to the thermal blanket materials. A multilayer thermal blanket has been designed at British Aerospace which has been proved to cope with adverse irradiation conditions of incident electron fluxes up to 100 nA/cm2. The main mode of charge removal is an enhanced leakage current which results in a much reduced surface potential and a notable absence of spontaneous discharges. This paper describes the principle of operation of this new thermal blanket and the tests carried out to prove its effectiveness." @default.
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- W2037454172 date "1982-02-01" @default.
- W2037454172 modified "2023-09-25" @default.
- W2037454172 title "A solution to the spacecraft charging problem" @default.
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- W2037454172 doi "https://doi.org/10.1016/0304-3886(82)90018-3" @default.
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