可折叠弹翼振动应力试验分析

Experiment Analysis of Vibration of a Foldable Wing

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, we use experimental displacement modality to replace the usually used experimental strain modality to calculate the stress response of wing type structures. The method proposed by us not only enhances the sensitivity, but also enlarges the frequency measurement range of the measured vibration data. So the precision of the calculated stress response is improved as confirmed by our results. Using the above method, we made detailed analysis for the vibration stress response of a foldable wing under transient shock load. Our theoretical and experimental research includes the natural characteristics secognition, shock response calculation(Eq.8) and shock stress analysis(Eq.13) for the foldable wing in 0, 30, 60, 90 degree positions respectively. Experimental analysis was made in Northwesten Polytechnical University for a certain type of foldable wing. We obtained its experimental displacement modality and then we worked out its shock stress response analysis.