全状态可测量导弹的积分滑模控制

Integral-Type Sliding Mode Control of Whole-State Measurable Missile

针对全状态可测量导弹过载控制系统，引入一类积分型滑模面，设计了变结构控制律．对导弹的过载和角加速度进行控制。然后构造Lyapunov函数证明其稳定性，最后，仿真结果表明了该方法的优良控制效果。

By introducing a kind of integral-type sliding surface, a variable structure control （VSC） law was designed to control the overload and the angle acceleration of whole-state measurable missile. And the stability of the system was proved by constructing a Lyapunov function. Finally, the simulation results are presented to show the excellent control effect of the proposed method.