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研究了战术导弹在穿越离散突风区域时弹体的动力学响应鲁棒控制,给出了导弹在穿越突风区时的运动方程、导弹结构动力学模型、“1-cos”突风模型和控制模型,其中不仅考虑了弹体在突风区的刚体运动,而且考虑了弹体位置及空气舵位置的结构动力学响应引起的附加攻角,突风对空气舵的滞后影响效果,以及空气舵控制舵偏引起的控制力等。通过算例研究了导弹在穿越突风过程中使用空气舵对弹体的结构动力学响应进行控制,及弹体H∞控制方法,设计了最优控制器。研究发现,施加控制后的弹体结构动力学响应明显衰减。
The dynamic response of the projectile is studied when the tactical missile passes through discrete gust areas. The equations of motion of the missile when it passes through the gust area, the dynamic model of the missile structure, the “1-cos” Model and control model, which not only consider the rigid body movement of the projectile in the gust area, but also consider the additional angle of attack caused by the structural dynamic response of the projectile position and the position of the air rudder and the effect of the gust on the hysteresis of the air rudder. As well as the control of the rudder control caused by the air rudder. A numerical example is given to study the structural dynamics response of the projectile using the air rudder and the H∞ control method of the projectile. The optimal controller is designed. The study found that after the control of the body structure dynamic response significantly decayed.