Abstract:
A half-empiric mathematical model was elaborated to describe polymeric cover outgassing process in open space conditions. The calculation was carried out to estimate film thickness that arises as a result of gaseous products nonequilibrium condensation at a sensitive surface. Source data were: a) experimentally obtained time functions of polymeric cover mass loss at different temperatures; b) the construction element temperature regime data; c) the construction element temperature changes according to its location towards the Sun. To carry out the calculation the construction element and the sensitive surface geometry is considered to be axisymmetric. As a result, the numerical values of the average as well as maximum and minimum film thickness for the whole exploitation period of the spacecraft.
Keywords:spacecraft, contamination, outgassing, mass loss, temperature regime of the spacecraft, mathematical model, modeling.
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