Abstract

This article defines a theoretical method to the progressive failure analysis of a laminated composite curved structure for an elastic shock absorber of a UAV (Unmanned Aerial Vehicle). Based on the continuous model, the theoretical method is presented for purposes of investigating the material failure and post-failure behavior of the laminated composite curved structure. This method is derived using the Ritz method and Hashin’s failure criteria. The validity of the theoretical method is verified by comparing the results of the finite element analysis. Finally, the theoretical method is applied to optimizing a laminated composite curved structure for an elastic shock absorber of a UAV to minimize the mass and maximize the shock absorption performance. Furthermore, the shock absorption performance of the optimized elastic shock absorber is confirmed by the finite element analysis (3D explicit dynamic analysis). The optimization result allows a database to be obtained on the structural characteristics of laminated composite curved structure for aerospace applications. Consequently, it is concluded that the theoretical method is well suited to the progressive failure analysis of a laminated composite curved structure for aerospace applications due to their relative simplicity and computational efficiency.

摘要

本文为无人飞行器（UAV）的弹性减震器的层状复合弯曲结构的渐进式破坏分析定义了一种理论方法。基于连续模型，提出了理论方法以研究层压复合弯曲结构的材料破坏和破坏后的行为。该方法是使用Ritz方法和Hashin的失效准则得出的。通过比较有限元分析的结果，验证了理论方法的有效性。最后，将理论方法应用于无人机的弹性减震器的叠层复合弯曲结构的优化，以最小化质量并最大化减震性能。此外，优化的弹性减震器的减震性能通过有限元分析（3D显式动态分析）得到确认。优化结果允许获得关于航空航天应用的层压复合弯曲结构的结构特性的数据库。因此，可以得出结论，由于其相对简单和计算效率高，因此该理论方法非常适合用于航空航天应用的层压复合弯曲结构的渐进式失效分析。