旋翼复合材料桨叶弹性剪裁减振研究

Vibration Reduction of Composite Rotors with Tailored Couplings

通过调整桨叶复合材料大梁的铺层角及其展向分布,提出了SA349直升机马赫数相似模型旋翼桨叶的3种挥舞弯曲-扭转弹性耦合方案并进行了弹性剪裁分析。在分析中采用19自由度弹性耦合中等变形梁单元模型,以SA349直升机飞行状态2的气动力作为桨叶预定气动载荷,计算并比较了不同耦合方案的桨根与桨毂振动载荷,验证了弹性剪裁在直升机减振设计中的有效性。

Four sets of Mach scale rotors of SA349 helicopter are designed, and four kinds of coupling distribution scheme are obtained by adjusting the ply angle and its distribution of the composite spar of blades. The full-coupled finite element beam model with 19 DOFs is selected as the structure model. The programmed aerodynamic force of the blades is based on SA349 helicopter at flight status 2. The vibratory hub loads of the rotors and blade root vibratory load with different couplings are calculated, and the effectiveness of composite tailored coupling in the helicopter vibration reduction design is validated.