Dynamics Analysis of Water Ditching of Deformable Helicopter  

作　　者：Sun Xuan Tong Mingbo Wang Zhengzhong 

机构地区：[1]Ministerial Key Discipline Laboratory of Advanced Design Technology of Aircraft,Nanjing University of Aeronautics and Astronautics [2]Science and Technology on Rotorcraft Aeromechanics Laboratory,China Helicopter Research and Development Institute

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2017年第6期720-732,共13页南京航空航天大学学报（英文版）

基　　金：funded by the International S&T Cooperation Program of China(No.2011DFR80210);the National Natural Science Foundation of China(No.11302105)

摘　　要：To understand the effect of attitude angle on helicopter water ditching,a finite element model(FEM)of helicopter water ditching was established via the nonlinear finite element method.Based on the LS-DYNA software,the finite element model of the helicopter was established.Different attitude of helicopter water ditching was simulated and analysed.Three pressure measuring points were arranged in the aircraft belly area.The pressure curves were provided seperately.Finally,the effects of attitude on helicopter water ditching was discussed,particularly the stability and the overload of helicopter.Through the contours of stress,it can be figured out that the maximum pressure locates at the position of aircraft belly where stiffness is larger.Then simulation and experimental results were compared.The difference of peak acceleration along the Z direction was small.Therefore,this method is feasible and helpful for the design of helicopter water ditching.To understand the effect of attitude angle on helicopter water ditching, a finite element model （FEM） of helicopter water ditching was established via the nonlinear finite element method. Based on the LS-DYNA soft- warethe finite element model of the helicopter was established. Different attitude of helicopter water ditching was simulated and analysed. Three pressure measuring points were arranged in the aircraft belly area. The pressure curves were provided seperately. Finally, the effects of attitude on helicopter water ditching was discussed, partic- ularly the stability and the overload of helicopter. Through the contours of stress, it can be figured out that the maximum pressure locates at the position of aircraft belly where stiffness is larger. Then simulation and experi- mental results were compared. The difference of peak acceleration along the Z direction was small. Therefore, this method is feasible and helpful for the design of helicopter water ditching.

关 键 词：water ditching HELICOPTER LS-DYNA SPH method 

分 类 号：V215.2[航空宇航科学与技术—航空宇航推进理论与工程]