基于终端滑模面的导弹滑模控制器设计

Design on Sliding Mode Controller of Missile Based on Terminal Sliding Mode Surface

为了研究滚转导弹的非线性控制特性,基于导弹简化的非线性动力学模型,采用基于趋近律的滑模控制器设计方法,设计了含有过载跟踪误差及其积分的自适应终端滑模面,使系统的状态在一开始到达并维持在滑模面上;采用双曲正切切换函数代替符号切换,以消除系统存在的抖振;根据滑模运动的渐进稳定性及其动态品质,设计满足要求的滑模变结构控制律;进行了控制算法的Simulink仿真。结果表明:在纵横向过载指令均为1的条件下,跟踪误差近似为0,说明滑模控制策略是解决滚转导弹非线性控制问题的有效方法之一。

To analyze the nonlinear control characteristics of rolling missile, according to the simplified nonlinear mode, the sliding mode control method based on the tending law was applied to design the adaptive terminal sliding mode surface including tracking error in acceleration and its integral function, and the state of control system can reach the sliding mode surface and be maintained. To eliminate chattering, the traditional index trending law was placed by the switching function of hyperbolic tangent. According to the stability in the sliding mode motion and dynamic quality, the sliding-mode variable- structure control law was designed. The Simulink simulation on control law was carried out. While the lon-gitudinal and lateral overload is 1g,the tracking error is almost zero. Sliding mode control is one of the effective methods to solve the nonlinear issues of missile.