抄録
Component arrangement in space satellite design is an important design factor for it has influence on many disciplines and cannot be modified in the latter detailed design phase. Nevertheless, actual satellite component arrangement design is left to the designer's experience and sense, hence not only it is difficult to find the optimal solution, but also it is hard to judge the quality of the obtained solution. This paper proposes a systematic design optimization method of the component arrangement of a small space satellite called "Micro-LabSat," which involves many constraints as in reality. The proposed method is a bi-level optimization procedure which consists of genetic algorithms to obtain the general location of each component and SQP to determine the detailed coordinates.
