星载伞状可展开天线支撑肋结构优化  

Optimization of the rib of the satellite deployable umbrella reflector

作　　者：王波[1] 郑士昆[1] 李洲洋[2] 谢卓 WANG Bo;ZHENG Shikun;LI Zhouyang;XIE Zhuo(Xi'an Institute of Space Radio Technology,Xi5an 710100,China;;School of Mechanical Engineering,Northwestern Polytcchnical Univ.,Xi’an 7 10072,China)

机构地区：[1]西安空间无线电技术研究所,陕西西安710100 [2]西北工业大学机电学院,陕西西安710072

出　　处：《西安电子科技大学学报》2018年第5期115-120,共6页Journal of Xidian University

基　　金：国家自然科学基金资助项目(51205322)

摘　　要：为减轻星载伞状可展开天线的质量,选取天线支撑肋为研究对象,通过对天线结构及支撑肋的受力分析,建立了以刚度为约束条件、以结构参数为设计变量、以质量最轻为目标的支撑肋结构优化模型.通过蒙特卡罗法和复合形法进行求解,得到了优化的支撑肋结构参数.优化后的支撑肋质量较优化前减轻了50.4%.优化结果表明,增加支撑肋截面高度和采用变截面结构是实现支撑肋轻量化的主要途径;相比蒙特卡罗法,复合形法在求解时具有更高的效率和稳定性.In order to reduce the mass of the satellite deployable umbrella reflector,a structure optimization model of the rib is established by analyzing the structure of the rib and forces on it.The minimum mass of the rib is calculated by optimizing its structure parameters under given rigidity and loads.Optimized structure parameters are obtained by solving the model with the Monte Carlo method and Compound Form method.Comparing the original structure,50.4%mass is successfully reduced after optimization.It is found that increasing the height of the rib's cross section and using a variable section are two effective ways to make the rib lighter,and that the Compound F^orm method has a better performance than the Monte Carlo method when solving this model.

关 键 词：伞状可展开天线 结构优化 蒙特卡罗法 复合形法 

分 类 号：V414.19[航空宇航科学与技术—航空宇航推进理论与工程]