航天器工程2017，Vol.26Issue(4)：22-28,7.DOI:10.3969/j.issn.1673-8748.2017.04.004
一种卫星分步结构优化方法
A Satellite Multi-step Structure Optimization Method
摘要
Abstract
During the design of satellite structure,in order to achieve weight reduction under vari ous working conditions,a multi step optimization method to optimize and design structure is proposed.First step,an optimal topology configuration is obtained by utilizing Solid Isotropic Material Penalty (SIMP) approach,considering minimization of compliance.The optimization objective under multiple loading cases is transformed into a single objective.The second step is to extract the topology configuration of the first-step,and the multi-objective optimization of shape and size parameters is achieved utilizing the Non-dominated Sorting Genetic Algorithm-Ⅱ(NSGA-Ⅱ) method.The third step,engineer conducts several rounds of redesign considering requirements of manufacture and assemblage and a new design is given.This method is applied to the design of the supporting leg of Tiantuo-3 satellite,which considering the topology optimization and multi-objective shape and size optimization under multiqoading cases.The mass reduction of supporting leg is 44.57％ and the satellite structural fundamental frequency is increased by 3.97％,which indicates that the method has strong engineering application value.关键词
卫星/拓扑优化/形状尺寸优化/多工况/多目标Key words
satellite/topology optimization/shape and size optimization/multiple loading cases/multi-objective分类
航空航天引用本文复制引用
徐皓,姚雯,赵勇,王宁,都柄晓..一种卫星分步结构优化方法[J].航天器工程,2017,26(4):22-28,7.基金项目
国家自然科学基金(51675525) （51675525）
