巡飞导弹纵向弹性动态特性分析

Longitudinal Elastic Dynamic Characteristics Analysis of Cruise Missile

为了设计巡飞导弹在弹性振动时的控制器,对其纵向动态特性进行了分析。采用NASTRAN软件计算了结构的固有模态,研究了弹性振动时的附加非定常气动力,采用线性化理论建立了刚体扰动运动方程组,将弹性振动引起的附加非定常气动力作为干扰输入项代入扰动运动方程组。从而得到了弹性振动下的动态响应。响应结果表明,在满足气动与结构稳定的前提下,弹性振动引起的纵向姿态变化量非常微小,对飞行稳定性不造成显著影响。

In order to design the controller of cruise missile vibrating in flight,the longitudinal dynamic characteristics of the missile are analyzed in this paper. The intrinsic mode is calculated by using NASTRAN. The additional unsteady aerodynamics derived from vibration is investigated. The longitudinal perturbation motion equations are established by the linearization theory. After the additional unsteady aerodynamics is fitted to the equations as disturbance variables,the dynamic response will be obtained. The results indicate that the longitudinal attitude variation will be very small when the aerodynamic and structure stability can be satified,and the elastic vibration will not influence flight stability.