A propulsion system implementation for a small satellite test case will serve as a reference example of the implemented algorithm application. Various degrees of freedom exist for a hardware-based sub-system design these are to be resolved via an evolutionary algorithm to determine an optimal system configuration. After deriving top-level estimates for each spacecraft sub-system based on heuristic heritage data, a detailed component-based system analysis follows. The capability of evolutionary algorithms to analyse and effectively design spacecraft (sub-)systems is shown. In this paper, a generic full-system estimation software tool is introduced and applied to a data set of actual flight missions to derive a heuristic for system composition for mass and power ratios of considered sub-systems.
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