微小卫星主承力结构设计与力学特性分析  

Design and Mechanical Characteristic Analysis of Main Load-bearing Structure of Microsatellite

作　　者：吴彬 黄晓萍 胡诗悦 Wu Bin;Huang Xiaoping;Hu Shiyue

机构地区：[1]南京机电职业技术学院机械工程系,南京211300

出　　处：《机械制造》2024年第11期56-59,共4页Machinery

基　　金：江苏高校“青蓝工程”项目(苏教师函[2024]14号);江苏高校哲学社会科学研究项目(编号:2023SJYB0820)。

摘　　要：微小卫星主承力结构主要采用由蜂窝铝板组成的箱板式结构,加工复杂,周期长。对此,设计了框架式微小卫星主承力结构。对所设计的主承力结构进行静力学分析,最大应力为9.025 MPa,小于材料的最大屈服应力,最大变形为0.087 mm,小于设计要求的沿坐标轴方向最大变形,满足强度和刚度要求。同时进行1阶至12阶模态分析,8阶模态前后两面向X轴正方向凹陷,出现最大位移83.293 mm,12阶模态整体沿Y轴方向扭转,出现最大振动频率613.15 Hz。力学特性分析结果为微小卫星主承力结构的振动与噪声研究提供了理论依据。Main load-bearing structure of microsatellite mainly adopts the box-type structure composed of honeycomb aluminum plate,which is complicated for processing and has a long cycle.Therefore,the frame main load-bearing structure of microsatellite was designed.The static analysis of the designed main load-bearing structure shows that the maximum stress is 9.025 MPa,which is less than the maximum yield stress of the material,and the maximum deformation is 0.087 mm,which is less than the maximum deformation in the direction of the coordinate axis required by the design,and meets the requirements of strength and stiffness.In the meanwhile,the mode analysis of order 1 to order 12 shows that the mode of order 8 is the front and back faces depressing in the positive direction of X axis,and the maximum displacement is 83.293 mm.The mode of order 12 is torsional in the direction of Y axis,and the maximum vibration frequency is 613.15 Hz.The analysis result of mechanical characteristic provides a theoretical basis for the study of vibration and noise of the main load-bearing structure of microsatellite.

关 键 词：卫星 承力 结构 设计 力学 分析 

分 类 号：V423.42[航空宇航科学与技术—飞行器设计]