大型空间可展开结构热致振动研究  

Thermally Induced Vibration Study for Large-Scale Deployable Spatial Structures

作　　者：胡甜赐 陈素芳 吴松 姜东[2,5] 费庆国[1,2] HU Tianci;CHEN Sufang;WU Song;JIANG Dong;FEI Qingguo(School of Mechanical Engineering,Southeast University,Nanjing 211189,Jiangsu,China;Institute of Aerospace Machinery and Dynamics,Southeast University,Nanjing 211189,Jiangsu,China;C.hengxian College,Southeast University,Nanjing 210088,Jiangsu,China;Aerospace System Engineering Shanghai,Shanghai 201109,China;College of Mechanical and Electronic Engineering,Nanjing Forest University,Nanjing 210037,Jiangsu,China)

机构地区：[1]东南大学机械工程学院,江苏南京211189 [2]东南大学空天机械动力学研究所,江苏南京211189 [3]东南大学成贤学院,江苏南京210088 [4]上海宇航系统工程研究所,上海201109 [5]南京林业大学机械电子工程学院,江苏南京210037

出　　处：《上海航天（中英文）》2021年第1期28-35,共8页Aerospace Shanghai（Chinese&English）

基　　金：上海航天科技创新基金资助项目(SAST2018024)。

摘　　要：搭载高精度光学载荷的空间飞行器在进出地球阴影区时,飞行器上处于展开状态的太阳帆板因剧烈的温度变化会诱发振动问题。本文采用有限元法,首先对太阳帆板进行在轨进出阴影区瞬态温度求解;然后基于卫星-太阳帆板整体动力学模型,将时变温度场等效为时变热载荷加载到整星系统上,对整星系统的热致振动动力学响应进行了数值模拟。结果表明:处于地球同步轨道的卫星-帆板在进出阴影区时,太阳帆板的温度变化较大,温差最高达到200℃;时变热载荷导致帆板结构和卫星姿态发生明显的振动响应。该方法可以合理地预测大型空间可展开系统热扰动响应。A vibration problem will be induced by the intense temperature change of the solar panel in.unfurled state on the spacecraft when it carries high precision optical load,entering and leaving the shadow region of the earth.The finite element method is employed to deal with this issue.First,the transient temperature of the solar panel in and out of the Earth's shadow region is solved.Second,the time-varying temperature field is equivalent to the time-varying thermal load on the whole satellite system based on the satellite-solar dynamics model,and the thermal-induced vibration dynamic response of the whole star system is numerically simulated.The results show that the temperature of the solar panel changes greatly when the satellite-panel enters and leaves the shadow area,and the temperature difference reaches up to 200℃.The time-varying thermal load results in obvious vibration response of the panel structure and satellite attitude.The proposed method could be used to reasonably predict the thermal induced response of a large-scale deployable system.

关 键 词：大型空间结构 热扰动 有限元法 时变热载荷 动力学响应 

分 类 号：V414[航空宇航科学与技术—航空宇航推进理论与工程]