充气机翼的褶皱与失效行为研究

在经典工程梁理论的基础上，结合张力薄膜的应力状态分析，提出充气机翼褶皱失稳的判据。计入表面薄膜褶皱引起的刚度退化效应，将机翼等效处理为一个变截面刚度的梁，建立了充气悬臂机翼的等效梁模型，并采用微分求积法进行充气机翼弯曲变形分析。计算结果与充气机翼的静力弯曲试验结果相吻合，验证了充气机翼弯曲变形分析方法的有效性。应用片条理论引入气动力模型，并与所建立的等效梁模型相耦合，建立充气机翼的静气动弹性耦合模型，并用迭代算法进行求解。考虑起皱和失稳两种判据，并计算获取了试验机翼的起皱动压和皱褶失稳动压形式，计算结果与风洞试验结果一致。根据所建立的充气机翼静气动弹性分析方法，可以预测充气机翼表面褶皱区的扩展和弯曲变形，进而绘制充气机翼的静气弹许用包线，为充气机翼的设计提供必要的安全边界参考依据。

Wrinkling and failure behavior research of inflated wing

Based on classical engineering beam theory, combined with the stress state analysis of tense membrane, the wrinkling and instability criterions of inflated wing are proposed. We consider stiffness degradation caused by wrinkle of inflated wing, and treat the inflated wing as a beam which possesses a variable section stiffness with the expansion of wrinkle; an equivalent beam model of inflated wing is established, and the differential quadrature method is applied to calculate the bending deformation of inflated wing. The calculated results are consistent with the experimental results from the static bending tests of inflated wing, and hence verify the effectiveness of the proposed deformation analysis method of inflated wing. We use the strip theory to introduce the aerodynamic model which is then coupled with the equivalent beam model of inflated wing, and thus a static aeroelastic model of inflated wing is developed, which applies an iterative method to solve. According to the wrinkling and instability criterions, we use the proposed model to calculate the critical wrinkle dynamic pressure and critical instability dynamic pressure of the experimental inflated wing, and the obtained results are consistent with the results from tunnel tests. Furthermore, the proposed model is used to predict the extending process of membrane wrinkled zone and bending failure load for the inflated wing, and then obtain the available static aeroelastic envelope curves of inflated wing under different criterion conditions, and provide necessary safety boundary analysis for the design of inflated wing.