基于非金属材料减振设计的小型空间飞行器模态分析  

Modal analysis on small spacecraft based on nonmetallic material vibration reduction design

作　　者：李海岩[1] 郭剑[1] 吕静[1] 王彬[1] 

机构地区：[1]中国运载火箭技术研究院研究发展中心,北京100076

出　　处：《计算机辅助工程》2013年第6期55-58,共4页Computer Aided Engineering

摘　　要：为有效改善发射过程中飞行器有效载荷的动力学环境,以某小型空间飞行器为例,基于转接框结构提出非金属材料减振设计方案.在有限元模型中采用考虑剪切变形的梁单元模拟非金属材料减振器,对飞行器的动特性进行数值仿真分析和试验验证.结果表明仿真结果与试验结果基本一致.To improve the dynamics environmenlL for spacecraft payload during launching effectively, taking a small spacecraft as an example, a nonmetallic material vibration reduction design scheme is proposed on the basis of adapter frame structure. The nonmetallic material vibration damper is simulated by beam element considering shear deformation in finite element model, and the numerical simulation analysis and experiments are performed on the dynamic characteristics of the spacecraft. The results show that the simulation results are well consistent with the experiment results.

关 键 词：空间飞行器 非金属材料 减振器 有效载荷 转接框 锤击测试 

分 类 号：V414.33[航空宇航科学与技术—航空宇航推进理论与工程] O313.7[理学—一般力学与力学基础]