变体机翼粘弹性材料连接蒙皮板结构的振动特性

Vibration Characteristics of a Morphing Wings Viscoelastic Material Connected Skin Plate Structure

摘要: 本文针对新能源变体飞机机翼后缘蒙皮拼接结构为研究对象进行了系统的研究，建立柔性蒙皮单元模型及其动力学方程。采用粘弹性材料与复合材料板连接模拟蒙皮柔性部分，将粘弹性材料部分等效为各向同性材料板。基于瑞利里兹法建立了柔性蒙皮单元不同铺层角度下的动力学方程。在自由边界处引入弹性弹簧模拟约束条件，得到了系统的耦合行为与动能势能关系，并探究了耦合角度变化对结构振动特性的影响。结果表明：本文所提出的方法与有限元仿真高度吻合，正确性得到了验证。铺层角度的改变，对固有频率以及振型具有显著影响，选取适当的铺层方向可以满足特定的工况。在一定范围内增加耦合角度，可以使结构整体固有频率明显上升。本文的研究为新能源飞机的机翼后缘变形提供了技术支持。

Abstract: In this paper, a systematic study is carried out for the new energy morphing aircraft wing trailing edge skin connecting structure as the research object, and the flexible skin unit model and its dynamic equations are established. The viscoelastic material is connected with the composite material plate to simulate the flexible part of the skin, and the viscoelastic material part is equivalent to the isotropic material plate. Based on the Rayleigh-Ritz method, the kinetic equations of the flexible skin unit under different layup angles are established. Elastic spring simulation constraints are introduced at the free boundary, and the coupling behavior and kinetic potential energy relationship of the system are obtained, and the effect of the change of coupling angle on the vibration characteristics of the structure is investigated. The results show that the method proposed in this paper is highly consistent with the finite element simulation, and the correctness of the method is verified. The change of the layup angle has a significant effect on the intrinsic frequency as well as the vibration pattern, and the appropriate layup direction can be selected to meet the specific working conditions. Increasing the coupling angle within a certain range can make the overall intrinsic frequency of the structure rise significantly. The research in this paper provides technical support for the deformation of the trailing edge of the wing of a new energy airplane.