由于当今导弹设计出现长径比逐渐增大的趋势,气动伺服弹性问题引起设计工作者的重视,气动伺服弹性是由于大长径比导弹表面的非定常气动力、导弹结构弹性与飞行控制系统之间的耦合带来的影响。基于此,文中对导弹气动伺服弹性问题进行介绍,考虑导弹刚体运动与弹性体运动之间的耦合作用,推导由于弹性振动带来的附加气动力和力矩,并考虑了由于弹体变形引起的推力偏心问题,利用弹性体导弹动力学模型,对弹性体导弹的气动伺服弹性进行仿真分析,并得到相关结论。

Because of the increasing trend of aspect ratio in missile design nowadays, the problem of pneumatic servo elasticity attracts the attention of designers. The pneumatic servo elasticity problem is caused by the unsteady aerodynamic force on the surface of missile with large aspect ratio, the coupling between missile structural elasticity and flight control system. Based on this, the pneumatic servo elasticity problem of missile is introduced in this paper. Considering the coupling effect between rigid body motion and elastic body motion, the additional aerodynamic force and moment caused by elastic vibration are derived, and the thrust eccentricity caused by elastic body deformation is considered. The eccentricity problem is simulated and analyzed by the elastic missile dynamic model, and the relevant conclusions are obtained.