【摘要】 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.更多还原

【Abstract】 A dynamic model was developed to investigate the elastic impact of helicopter rotor blades.General kinematical relations for a beam theory were established to treat the finite rotation.Hertz’ theory of elasticity was presented to treat local elastic deformation.The compatibility equation of displacement was adopted to calculate the impact loads.Dynamic equations of elastic impact of rotor blades were derived by Hamilton principle.In comparison with Timoshenko’s example,the validity of the results has been demonstrated.The impact response of helicopter blades under the impact of a lumped mass was also discussed.更多还原