含损伤复合材料层合板振动特性研究

本文旨在找出损伤对复合材料层合板振动特性的影响。复合材料在直升机桨叶上的应用，实现了桨叶优化设计，改善了旋翼气动性能，使桨叶的寿命增加到上万小时，甚至达到无限寿命。因此，使用复合材料已成为现代直升机桨叶的发展趋势。对G827／3234、G803／3234以及G814／3234等三种铺层材料的复合材料层合板进行了振动试验研究与理论分析，得到了振动特性与材料、铺层方式的关系。进一步对这些层合板在含有穿孔、分层损伤情况下的振动特性进行了研究。结果表明，理论分析结果与试验结果吻合，证明了所建模型的有效性。该研究结果对直升机复合材料桨叶结构损伤容限分析与设计具有一定的参考价值。

Vibration Performance of Composite Laminates with Damage

The present work is to study the effect of damage on the vibration performance of composite laminates. The use of composite materials to helicopter blades implements the optimization design of blades, improves the aero-dynamical performance of airfoils, and greatly increases the lifespan of blades. So composite materials will be widely used in helicopter blades. Vibration tests and theoretical analysis were carried out on the composite laminates made of three kinds of composites G827/3234, G803/ 3234 and G814/3234. The effect of the laminte material and ply sequence of the composite laminates on the vibration performanee was obtained. Then the vibration performance of the laminates with a hole or delamination damage was studied. It is shown that the results of theoretical analysis are consistent with the experiment results, which proves the validity of the model. The study results are of value for the damage tolerance analysis and design of the helicopter composite rotor blades.