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航天器部件因热诱发的弯扭耦合振动会发生破坏。为了解热诱发弯扭耦合振动的机理,发展了一种14个自由度的二节点开口薄壁梁单元。该单元综合考虑了翘曲、预应力与热应变的影响,得到特有的质量阵、刚度阵和载荷阵。与其他类型梁单元组集后,通过模态分析的方法,得到整个结构的动力学响应。对Hubble太空望远镜的太阳能帆板,用该方法求得的固有频率和固有振型的数值解与近似理论解符合甚好。该分析解释了热使太阳能帆板发生扭转破坏的原因。
Spacecraft components due to heat induced bending and torsional vibration coupling will occur damage. In order to understand the mechanism of thermally induced bending-torsional coupled vibration, a 14-DOF, two-node, open-ended thin-walled beam element was developed. The unit takes into account the effects of warpage, prestress and thermal strain, and obtains the unique mass, stiffness and load matrices. After grouping with other types of beam elements, the dynamic response of the whole structure is obtained through modal analysis. For the solar panel of the Hubble Space Telescope, the numerical solutions of the natural frequency and the natural mode obtained by this method are in good agreement with the approximate theoretical solution. This analysis explains why heat causes the solar windsink to twist and ruin.