摘要
国内太阳翼预紧力绝大多数由压紧释放装置中的压紧杆提供,在卫星发射阶段,当太阳翼压紧杆的预紧力不足时,太阳翼与卫星本体会出现耦合现象,对太阳翼的结构特性和在轨展开产生一定的影响。文章提出采用有限元仿真计算与振动试验相结合的方式对太阳翼压紧杆的预紧力进行研究,针对某型号太阳翼完成了振动试验。试验结果表明:压紧杆预紧力由3000N递减到1000N时,太阳翼一阶频率减小约7Hz,同时太阳翼的最大响应值增大约0.5g,最大响应值较输入值X方向放大约20倍,Y方向放大约7倍,Z方向放大约17倍。因此,振动试验获知的数据可以更准确反映太阳翼压紧杆预紧力对其结构特性的影响。
The most of the pre-tightening force of the solar wing is provided by the compression bar.During the satellite launch stage,when the pre-tightening force of the compression bar is insufficient,the frequency coupling will occur between the solar wing and the satellite,which will have a certain impact on the structural characteristics of the solar wing and the on-orbit deployment.In this paper,the pre-tightening force provided by the compression bar of the solar wing is studied by the method of finite element simulation and vibration test.The vibration test is completed for a certain type of solar wing.The results show that When the pre-tightening force of the compression bar decreases from 3000N to 1000N,the fundamental frequency of the solar wing decreases by about 7Hz,and the maximum response value increases by about 0.5g.The maximum response value is about 20 times larger than the input value in the X direction,and about 7 times larger in the Y direction,about 17 times in the Z direction.Therefore,the vibration test data can more accurately reflect the influence of the pre-tightening force provided by the compression bar of the solar wing on its structural characteristics.
作者
张燕娜
Zhang Yanna(The 39th Research Institute of China Electronics Technology Group Corporation,Xi’an 710065;Key Laboratory of Atenna and Control Technology of Shanxi Province,Xi’an 710065)
出处
《航天制造技术》
2023年第1期45-50,共6页
Aerospace Manufacturing Technology
基金
陕西省自然科学基础研究计划(天地一体化信息网络)。
关键词
太阳翼
压紧杆
预紧力
模态分析
振动试验
solar wing
compression bar
pre-tightening force
modal analysis
vibration test
