摘要
针对某一2 m口径卫星反射器工程模型,介绍了反射器各部件的有限元建模方法及材料参数,各部件包括蜂窝夹层结构、背架管件以及背架和反射面连接角片.分析了在同步轨道极端高低温温度场下,反射器在展开工作状态的热变形及指向精度变化.根据在轨热变形最小的原则,采用离散数据对比分析的方法,对反射器背架截面参数、背架管件厚度、角片连接方式、角片连接密度等参数进行优化,得到了这些参数的最优设计值,完成了反射器结构工程模型的优化方案.
The finite element modeling method and material parameter valuing method were presented for a 2 m diameter satellite reflector engineering model,including the honeycomb sandwich structure,the back-frame tubes and the patches connecting the back frame and the reflector. The thermal deformation and the variation of pointing accuracy in unfolded work condition of the reflector under extreme high/low temperatures were analyzed. Based on the principle of minimum in-orbit thermal deformation,the optimal design values of the parameters,including the section parameters of the back-frame,the thickness of the back-frame tubes,the connection mode and the density of patches,were obtained by means of the discrete data comparative analysis method. The structural optimization of the reflector engineering model was fulfilled.
作者
李岩咏
韦娟芳
江文剑
LI Yanyong;WEI Juanfang;JIANG Wenjian(Space Structures Research Center, Zhejiang University, Hangzhou 510058, P.R. China;Xi＇ an Institute of Space Radio Technology, Xi＇ an 710100, P.R. China)
出处
《应用数学和力学》
CSCD
北大核心
2018年第6期657-664,共8页
Applied Mathematics and Mechanics
基金
中国航天科技集团公司航天科技创新基金(JSKFJ201604120011)对本文的资助
关键词
卫星
反射器
热变形
结构优化
satellite
reflector
thermal deformation
structural optimization
