基于动态ニ阶滑模控制算法的导弹自动驾驶仪设计

尾控型侧滑转弯( STT)导弹过载输出跟踪模型具有非最小相位的特性，系统的零动态或内部动态不稳定，所以不能直接应用反馈线性化和滑模控制等算法设计导弹过载输出控制器。为了设计方便，首先将导弹数学模型的线性部分进行规范形转化；然后将输出跟踪问题转化为状态跟踪问题，则可采用滑模控制设计自动驾驶仪。通过构造动态滑模输出，使得系统零动态稳定；采用全局二阶滑模控制来消除抖振。仿真结果表明，所提出的方法可使导弹的输出过载准确跟踪制导指令，而且切换抖动得到有效抑制。

Missile Autopilot Design Based on Dynamic Second Order Sliding Mode Control

A non-minimum phase nonlinear missile model is used to design a stable controller.Its non-minimum phase characteristic restricts direct applications of some powerful nonlinear control techniques,such as feedback linearization control and sliding mode control(SMC).For convenience in the design,the linear part of the system model was transformed to the normalized form first.The output-tracking problem would be replaced by the state tracking problem,hence,the sliding mode control could be used for the autopilot design.Valid dynamic sliding mode output that guarantees the system stable zero dynamics was constructed,and a global second order sliding mode control was adopted to circumvent chattering phenomena.The simulation results show the validity of the proposed method in command tracking and chattering attenuation.