Structural modeling and design optimization of spacecraft

This paper presents an application of finite element (FE) modeling and structural optimization techniques to the design of a spacecraft structure system. The system mainly consists of honeycomb panels, reinforced cylindrical shell, upper frame and various non-structural masses attached. A serious of simplifications is adopted to develop FE model of such a complex engineering system. With the FE model, non-linear optimization and analysis modules as well as a man-machine interactive method are combined to minimize the weight of the structure system: first, the cross-sectional variables are optimized by numerical algorithm (two-level multipoint constraints approximation method), and later the topology variables are adjusted with man-machine interactive ways, then by means of an iterative process of the two steps, the weight is cut down gradually. The application results show that the FE model is reasonable and the optimization method works satisfactorily and effectively.