基于ANSYS的可变后掠角机翼结构稳定性分析

摘要

With 6 sets of different sweep wing in same lfight condition, lfight state, under the same wing area, analyzed the lift and drag performance, and based on Hypermesh, ANSYS software, the ifnite element numerical simulation of the 6 sets of wing were taken, to get the stress and the maximal displacement cloud image. The calculation and analysis indicated that, under the same lfight state and same wing projection area, the impact of strength was relatively smal , and stiffness increased gradualy when the sweep angle increases. This paper can provide a reference for the selection and performance analysis of the sweep when designing the wing.%在相同的飞行条件下，对6组面积相同但后掠角不同的机翼的升力/阻力特性进行了分析，并基于Hypermesh、ANSYS等软件对6组机翼分别进行强度及刚度的有限元数值模拟，得到应力及最大位移云图。通过计算分析可知，相同飞行状态和相同机翼投影面积下，机翼后掠角对强度影响相对较小，对刚度影响较大。可为机翼设计时后掠角的选择及性能分析提供参考。