MULTI-BODY AEROELASTIC STABILITY ANALYSIS OF TILTROTOR AIRCRAFT IN HELICOPTER MODE  

直升机模式下倾转旋翼机多体气弹动力稳定性分析(英文)

作　　者：董凌华[1] 杨卫东[1] 夏品奇[1] 

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2006年第3期161-167,共7页南京航空航天大学学报（英文版）

基　　金：国家"八六三"高技术研究发展计划资助项目。~~

摘　　要：The muhi-body analysis of the aeroelastic stability of the tiltrotor aircraft is presented. Muhi-body dynamic differential equations are combined with the equations of the unsteady dynamic inflow model to establish the complete unsteadily aeroelastic coupling analytical model of the tiltrotor. The stability of the tiltrotor in the helicopter mode is analyzed aiming at a semi span soft-inplane tihrotor model with an elastic wing. Parametric effects of the lag stiffness of blades and the flight speed are analyzed. Numerical simulations demonstrate that the multibody analytical model can analyze the aeroelastic stability of the tiltrotor aircraft in the helicopter mode.通过多体动力学方法建立了倾转旋翼机动力学分析模型。结合动力入流,研究了直升机模式下倾转旋翼机非线性非定常气弹耦合动力学特性。集成了非定常动态入流方程与倾转过渡状态的多体动力学方程,建立了倾转旋翼机时域非定常气弹耦合分析模型。以半展长弹性机翼全铰接式倾转旋翼机模型为例,在直升机模式下分析了桨叶摆振刚度及飞行速度对倾转旋翼机气弹稳定性的影响。数值计算表明建立的多体动力学模型能够快速分析直升机模式下倾转旋翼机复杂的旋翼/机翼气弹耦合动力学特性。

关 键 词：TILTROTOR HELICOPTER aeroelastic stability multi body dynamics dynamic inflow 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]