基于Patran/Nastran的某卫星主承力结构优化设计  

Optimization design of satellite’s main structure based on Patran∕Nastran

作　　者：徐欣 刘江[1,2] 田宗军 施思寒[1] XU Xin;LIU Jiang;TIAN Zongjun;SHI Sihan(DFH Satellite Co.,Ltd.,Beijing 100094;College of Mechanical and Electrical Engineering,Nanjing University of Aeronautics&Astronautics,Nanjing 210016;Nanjing HANGPU Machinery Technology Co.,Ltd.,Nanjing 210016)

机构地区：[1]航天东方红卫星有限公司,北京100094 [2]南京航空航天大学机电学院,江苏南京210016 [3]南京航浦机械科技有限公司,江苏南京210016

出　　处：《机械设计》2024年第8期82-88,共7页Journal of Machine Design

基　　金：空间碎片与近地小行星防御科研项目(KJSP2020010402)。

摘　　要：针对某卫星主体结构采用传统尺寸设计方法后无法满足运载承载刚度要求的问题,文中采用Patran/Nastran的Optimization模块,以结构刚度为设计约束,以整星总质量为目标函数,对卫星主体结构进行了尺寸优化设计,优化后的主结构通过有限元分析与试验验证。结果表明:经优化后卫星总质量为169.4 kg,与优化前质量几乎一致,但优化后主结构1阶固有频率较优化前提高了30%,达到了59.87 Hz,与理论分析值57.03 Hz基本吻合,满足运载承载刚度不小于55 Hz的要求;优化后主结构成功通过2.5倍鉴定级的超载载荷考核,达到了预期设计值;卫星已顺利通过地面静力试验、整星系统级振动试验和主动段发射飞行验证,具备高刚度和高强度的结构承载能力。文中的工程经验可为同类型小卫星结构优化设计提供参考。Since the satellite’s main structure fails to meet the requirement of carrying stiffness when the traditional method of size design is adopted,in this article the Optimization Module of Patran∕Nastran is used for size optimization,with the structural stiffness as the design constraint and the satellite’s total mass as the objective function.The optimized main structure is verified through the finite-element analysis and experiments.The results are as follows.After optimization,the satellite’s total mass is 169.4 kg,which is almost the same as that before optimization.However,the main structure’s first-order natural frequency after optimization increases by 30%,compared to that before optimization,reaching 59.87 Hz,which is basically consistent with the theoretical value of 57.03 Hz and meets the requirement of carrying stiffness-not less than 55 Hz.After optimization,the main structure successfully passes the overload assessment,which is 2.5 times as much as the appraisal level,which complies with the expected design value.The satellite successfully passes the ground static test,the whole system vibration test,and the activephase launching flight verification,with desirable stiffness and high-strength structural load-bearing capacity.The study on satellite engineering provides reference for optimized structure design of similar small satellites.

关 键 词：卫星结构 尺寸优化 有限元分析 试验验证 

分 类 号：V414[航空宇航科学与技术—航空宇航推进理论与工程]