直升机旋翼桨叶的弹性碰撞动力学建模  

Dynamic model of elastic impact of helicopter rotor blades

作　　者：王益锋[1] 王浩文[2] 高正[1] 

机构地区：[1]南京航空航天大学航空宇航学院直升机旋翼动力学重点实验室,南京210016 [2]清华大学航天航空学院,北京100084

出　　处：《航空动力学报》2009年第9期2046-2050,共5页Journal of Aerospace Power

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.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 d...

关 键 词：直升机 有限转动 弹性碰撞 响应 载荷 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]