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利用变结构跟踪控制理论设计了战术导弹大机动飞行时的姿态角控制系统，并进行了仿真研究，结果表明了所设计的控制律有效。
The attitude control system of tactical missile during maneuvering flight is designed by using variable structure tracking control theory. The simulation study is conducted and the results show that the designed control law is effective.