空间站柔性太阳翼热诱发振动分析

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摘要柔性太阳翼随空间站在轨运行时会受到周期性的热载荷作用，为研究热载荷对柔性太阳翼的影响，采用热-结构非耦合分析方法对柔性太阳翼进行了热诱发振动分析。提出了等效位移法，按照节点位移等效原则计算柔性太阳翼有限元模型各节点的等效温度载荷，再以该载荷为激励计算柔性太阳翼的动态响应。通过自编的Python程序实现等效温度载荷计算过程中的数据处理，以及热诱发振动分析流程中的有限元前后处理。通过与理论解和数值解作对比，验证了基于等效位移法求解等效温度载荷并用于非耦合热诱发振动分析的方法的准确性。通过对柔性太阳翼的热诱发振动分析，得到了柔性太阳翼的动态响应数据，发现了柔性太阳翼出地球阴影区时的刚柔耦合情况。分析结果可以为柔性太阳翼的设计和改进以及在轨的安全性、可靠性的评估提供参考。

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	孔祥宏
	王志瑾

关键词 ：柔性太阳翼, 热诱发振动, 位移等效原则, 等效温度载荷, 刚柔耦合

Abstract：The flexible solar wing(FSW) suffers from periodic thermal load when running on orbit with space station. In order to investigate the effect of thermal load on the FSW, an uncoupled thermal-structural analysis method is used to thermally induced vibration analysis(TIVA) of the FSW. Finite element(FE) method and equivalent displacement principle of nodes are used to calculate the equivalent temperature loads(ETLs) of the nodes of FSW’s FE model and then calculate the dynamic response of the FSW under the ETLs. Self-compiled Python programs are used to process the data for the calculation of ETLs and complete FE pre and post-processing for TIVA. Compared with the theoretic and numerical results, it is proved that the TIVA method is accurate. By the TIVA, the dynamic response of FSW is gotten, and the rigid-flexible coupling phenomenon of FSW is found out. The result of TIVA can offer a reference to design and improvement of FSW, and can also be used to assess the security and reliability of FSW.

Key words： flexible solar wing thermally induced vibration equivalent displacement principle equivalent temperature load rigid-flexible coupling

收稿日期: 2014-01-08 出版日期: 2015-03-15

引用本文:

孔祥宏，王志瑾. 空间站柔性太阳翼热诱发振动分析[J]. 振动与冲击, 2015, 34(5): 220-227.
KONG Xiang-hong, WANG Zhi-jin . Thermally Induced Vibration Analysis of Space Station’s Flexible Solar Wing. JOURNAL OF VIBRATION AND SHOCK, 2015, 34(5): 220-227.

链接本文:

http://jvs.sjtu.edu.cn/CN/ 或 http://jvs.sjtu.edu.cn/CN/Y2015/V34/I5/220

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