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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 the cruise missile during the elastic vibration, its longitudinal dynamic characteristics are analyzed. The inherent mode of the structure was calculated by NASTRAN software and the additional unsteady aerodynamics of the elastic vibration were studied. The equations of motion of the rigid body perturbation were established by using the linearization theory. The additional unsteady aerodynamic force caused by the elastic vibration was substituted as the disturbance input Perturbation equations of motion. Thus the dynamic response under elastic vibration is obtained. The response results show that under the precondition that the aerodynamic and structural stability are satisfied, the change of longitudinal attitude caused by elastic vibration is very small, which has no significant effect on flight stability.