Topology Optimization of Parts in A Satellite Structure under Stress and Frequency Constraints
At the early design stage of a satellite structure, it is desirable to consider topology optimization of some key parts as well as sizing parameters. Finite element model of the satellite is established according to the original design. In order to take both kinds of design parameters into account, a twostage optimization procedure is implemented by taking minimum weight as the design objective. First, topology optimizations based on SIMP concept are carried out under frequency constraints and stress constraints, respectively, in which two-level multipoint approximation algorithm and full-stress method are applied as the optimizer and optimality criteria Topology optimization results are obtained with shell elements, which are then transformed into frame structure with beam elements. Second, taking the cross-sectional dimensions of the obtained beams and other size parameters as design variables, the structure is further optimized. Both stages are implemented through a new developed module by PCL (Patran Command Language) on the base of MSC. Patran/Nastran. Through the optimization, reasonable topology of the key parts is obtained, the satellites static and dynamic performance is improved while its weight is reduced, which provides reference to the real structure design.
topology optimization frequency stress engineering
Wang Wei Chen Shenyan
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
748-751
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）