旋转弹体尾翼片非线性动载荷响应特性分析

Analysis of nonlinear dynamic load response characteristics of rotating projectile tail fins

旋转弹体在非稳态带攻角飞行时,可晃动尾翼片可能在较低转速下因低频动载荷响应过大造成结构提前断裂。针对旋转弹体尾翼片的动载荷响应破坏问题,建立了一种存在间隙的尾翼片在离心力以及非定常气动力作用下的非线性动载荷响应分析模型。对该系统的动力学方程进行数值求解,并使用Matlab/Simulink软件平台进一步开发尾翼动响应分析工具。通过调整尾翼片可晃动量e和载荷振荡因子k,研究了旋转弹体尾翼片的非线性动载荷响应特性,并指出旋转弹体在非稳态带攻角飞行时,可晃动尾翼片因倍周期低转速振动放大而可能提前发生破坏。

When the rotating projectile is flying at an unsteady angle of attack,the shakable tail flap may break the structure in advance due to the large response of low-frequency dynamic load at a low speed.Aiming at the dynamic load response failure of rotating projectile tail fins,a nonlinear dynamic load response analysis model of the tail fin with the gap is established under the action of centrifugal force and unsteady aerodynamic force.The dynamic equation of the system is solved numerically,and the tail dynamic response analysis tool is further developed by using MATLAB/Simulink software platform.By adjusting the e coefficient of the flapping momentum of the tail fin and the k coefficient of the load oscillation,the nonlinear dynamic load response characteristics of the tail fin of the rotating projectile are studied.It is revealed that the shaking tail fin may be damaged in advance due to the amplification of period-doubling low-speed vibration when the rotating projectile flies at an unsteady angle of attack.