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建立了直升机旋翼桨叶弹性正碰撞的动力学模型,采用有限转动梁理论处理桨叶的弹性变形,利用Hertz接触理论处理局部弹性变形,引入位移协调方程识别弹性碰撞载荷,运用Hamilton原理建立了桨叶正碰撞的动力学方程.通过与Timoshenko算例的对比表明了该方法的正确性,且对集中质量与直升机桨叶的弹性正碰撞问题进行了研究.
The dynamic model of helicopter rotor blades with positive elastic impact is established. The finite element method is used to deal with the elastic deformation of the blades. The Hertz contact theory is used to deal with the local elastic deformation. The displacement coordination equation is introduced to identify the elastic impact load. The dynamic equation of the collision of the positive and the negative blades is obtained. The correctness of the method is verified by comparison with the case of Timoshenko, and the problem of the positive collisions between the concentrated mass and the helicopter blades is studied.