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讨论可折叠弹翼在展开过程中的冲击振动及冲击振动应力的试验分析方法，建立了通过位移模态预估冲击应力的方法。
In this paper, the experimental and analytical methods of impact vibration and shock vibration stress of the folded wing during deployment are discussed, and a method of estimating impact stress through displacement mode is established.