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Among the mitigation measures introduced to cope with the space debris issuethere is the de-orbiting of decommissioned satellites. Guidelines forre-entering objects call for a ground casualty risk no higher than 0.0001. Tocomply with this requirement, satellites can be designed through adesign-for-demise philosophy. Still, a spacecraft designed to demise has tosurvive the debris-populated space environment for many years. The demisabilityand the survivability of a satellite can both be influenced by a set of commondesign choices such as the material selection, the geometry definition, and theposition of the components. Within this context, two models have been developedto analyse the demise and the survivability of satellites. Given the competingnature of the demisability and the survivability, a multi-objectiveoptimisation framework was developed, with the aim to identify trade-offsolutions for the preliminary design of satellites. As the problem is nonlinearand involves the combination of continuous and discrete variables, classicalderivative based approaches are unsuited and a genetic algorithm was selectedinstead. The genetic algorithm uses the developed demisability andsurvivability criteria as the fitness functions of the multi-objectivealgorithm. The paper presents a test case, which considers the preliminaryoptimisation of tanks in terms of material, geometry, location, and number oftanks for a representative Earth observation mission. The configuration of theexternal structure of the spacecraft is fixed. Tanks were selected because theyare sensitive to both design requirements: they represent critical componentsin the demise process and impact damage can cause the loss of the missionbecause of leaking and ruptures. The results present the possible trade offsolutions, constituting the Pareto front obtained from the multi-objectiveoptimisation.

Spacecraft design optimisation for demise and survivability