Abstract
The optimisation process that is treated in this paper performs an optimisation of the design of protection systems of spacecraft against micrometeoroids and space debris impacts. It yields a shield configuration that hasa minimum mass while at the same time it will have to satisfy a number of boundary conditions. The most important being the compliance with a predefined safety against penetration. In preceding work an optimisation algorithm consisting of a two step approach has been established [1]. During the application of this method a number of problems have been identified, which obstruct a useful optimisation. Those problems are the choice of ballistic limit equations used to calculate the number of penetrations or probability of no penetration, the mass calculation, particularly the inclusion of the influence of spacing, and the selection of effective optimisation variables. Those problems are addressed in this paper.
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