飞机机翼结构动力学特性研究

Research on Dynamic Characteristics of Aircraft Wing Structure

由于飞机在高速飞行时会引起机翼发散振动,引起飞机结构损坏,传统提高刚度的方法会大幅增加飞机重量。为解决上述问题,提出在机翼表面敷设约束阻尼层结构提高机翼动力学特性的方法。建立复合材料为基层的约束阻尼层结构的模型,并通过Patran/Nastran仿真分析粘弹性层厚度、约束层厚度和粘弹性层剪切模量对结构阻尼性能的影响。仿真结果表明,粘弹性层厚度和约束层厚度对复合结构模态频率和损耗因子具有相同的影响规律,而粘弹性层剪切模量不宜作为选择材料的依据。通过分析不同参数对类悬臂梁薄壁结构阻尼性能的影响,为高阻尼性能的机翼优化设计提供了参考。

Aiming at the characteristics of plane wing divergence vibration in high speed flight and to avoid the disadvantages of traditional method of increasing stiffness which will substantially increase the airplane weight, we proposed a method to improve the dynamic characteristics of the wing by laying constrained damping layer structure on the surface of wing. Establishing the finite element modal of constrained damping layer which uses the composite material as the basic layer, the effects of viscoelastic layer thickness, constrained layer thickness and shear modulus of viscoelastic layer on structural damping properties were analyzed by Patran/Nastran simulation software. The simulation results show that the effects of viscoelastic layer thickness and constrained layer thickness on composite structure modal frequencies and loss factors have the same pattern, and the viscoelastic material shear modulus is not suitable for the basis to choice the material. The analyses for the effects of different parameters on the cantilever beam of thin -walled structure on damping performance can provide some reference for the design of high damping properties of the wing.