星载双反射抛物面天线热变形分析  

Thermal deformation analysis on reflection surface of space-borne dual reflector parabolic antenna

作　　者：张兴丽[1] 朱德鑫 叶东[2] ZHANG Xingli;ZHU Dexin;YE Dong(College of Mechanical and Electrical Engineering,Northeast Forestry University,Harbin 150040,China;Institute of Satellite Technology,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]东北林业大学机电工程学院,哈尔滨150040 [2]哈尔滨工业大学卫星技术研究所,哈尔滨150001

出　　处：《航天器环境工程》2022年第6期569-574,共6页Spacecraft Environment Engineering

基　　金：国家自然科学基金项目(编号:51706039);中央高校基本科研业务费专项资金项目(编号:2572020BF01)。

摘　　要：星载天线在轨运行时受到空间外热流的影响,会经历周期性的高低温交变,导致其反射面产生热变形。为了保证星载天线稳定运行,选取某型号星载双反射抛物面天线作为研究对象,采用有限元法对天线高温工况下的在轨温度场进行分析,进而将天线上分布的温度载荷作为边界条件映射到结构场中进行热变形分析;同时详细分析了材料属性、铝蜂窝芯厚度、碳纤维贴层厚度、反射面支撑约束位置等因素对双反射抛物面天线热变形的影响,以期为星载天线结构优化设计提供理论参考。The space-borne antenna is affected by the heat flow in orbit.The antenna will experience periodic alternating high and low temperatures,resulting in thermal deformation of the antenna reflector.In order to ensure the stable operation of the space-borne antenna,a dual reflector parabolic antenna was selected as the research object in this paper.The finite element method was used to analyze the in-orbit temperature field of the antenna under high temperature.The temperature loads distributed on the antenna were then mapped as the boundary conditions to the structural field for thermal deformation analysis.The effects of the material properties,the aluminum honeycomb core thickness,the carbon fiber layer thickness,and the constrained positions of the reflector on the thermal deformation of dual reflector parabolic antenna were analyzed in detail to provide a theoretical reference for the optimization design of the space-borne antenna structure.

关 键 词：天线反射面 热变形 有限元法 蜂窝夹层结构 

分 类 号：V445.8[航空宇航科学与技术—飞行器设计] V439