导弹姿态的反演法控制器设计

Design of Backstepping Method Controller for Missile Attitude

反演法控制器,将导弹姿态角作为系统控制对象。控制器根据给定的俯仰角、偏航角和滚动角参考信号,得出相应的舵偏输入,使导弹能按给定姿态角确定的轨迹飞行。定点及全空间仿真结果证明,该控制器设计可行。

The missile attitudes were taken as the control objects of system by backstepping method controller. According to given reference signals of pitching angle, drifting angle and rolling angle, the relative rudder deviation inputs were calculated by backstepping controller. So the missile could be flied along the trace in decided attitude angle. The controller was approved feasibly by fixed point and total space simulation.