The invention provides a large-scale space structure thermally induced vibration equivalent test method. The method comprises the following steps: measuring the fundamental frequency of a horizontally placed large-scale space structure full-size test piece in an atmospheric environment; the method comprises the following steps: designing and developing a cut-off test piece consistent with a cross section structure of a large space structure, applying transient external heat flow to the cut-off test piece in a vacuum environment, and measuring the thermal response time of the structure; carrying out numerical simulation calculation on the large space structure full-size test piece to obtain quasi-static displacement of the structure; according to the fundamental frequency of the full-size test piece obtained through the test, the thermal response time of the cut-off test piece and the quasi-static displacement of the full-size test piece obtained through numerical simulation, the on-orbit thermally induced vibration amplitude of the full-size test piece is obtained through formula calculation. The method is simple and reliable, development of the spacecraft structure is facilitated, the development risk is reduced, and the development efficiency is improved.
本发明提供一种大型空间结构热致振动等效试验方法,所述方法包括:在大气环境下测量水平放置的大型空间结构全尺寸试验件的基频;设计研制与大型空间结构的截面结构一致的截断试验件,在真空环境下,对截断试验件施加瞬态外热流,测得结构的热响应时间;对大型空间结构全尺寸试验件进行数值仿真计算,获得结构的准静态位移;根据试验获得的全尺寸试验件基频,截断试验件的热响应时间,以及数值仿真获得的全尺寸试验件的准静态位移,通过公式计算获得全尺寸试验件在轨热致振动振幅。该方法简单可靠,有利于航天器结构的研制,降低研制风险、提高研制效率。
Large space structure thermally induced vibration equivalent extrapolation test method
一种大型空间结构热致振动等效外推试验方法
2023-11-03
Patent
Electronic Resource
Chinese
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