战术导弹自动驾驶仪变结构控制设计与仿真

Design and Simulation of Tactical Missile's Autopilot Based on Variable Structure Control

为了使战术导弹自动驾驶仪对导弹的内在参数变化等因素有较强的适应能力和鲁棒性并保证系统能够达到期望的性能指标要求,根据变结构理论对其进行了重新设计。先把战术导弹的典型自动驾驶仪回路简化为二阶线性变参数模型,并根据一条弹道上的导弹自动驾驶仪参数计算出其参数的变化范围。经严格推导了系统存在滑动模态的充分条件下设计了滑模变结构控制器对其进行控制。结论是,变结构控制方法对导弹内在参数大范围剧烈变化和外在环境扰动等因素具有较强的适应能力和鲁棒性。通过数字仿真验证了所设计的滑模变结构控制方法的正确性和有效性。

In this text, in order to make the tactical missile＇ s autopilot possess strong adaptive ability and robust character to the change of missile＇ s inner parameters and ensure system＇ s performance to reach the required specification, the tactical missle＇ s autopilot is redesigned according to the theory of variable structure control. Firstly, the autopilot of tactical missile is simplified as a second order model with variational parameters, the change range of these changeable parameters is calculated and obtained according to the missle autopilot＇ s parameters of one ballistic trajectory. Secondly, the sufficient condition of the existence of sliding mode is severely deduced, on the basis of it, a variable structure controller is designed to control the autopilot. The result is that the control method of variable structure control possesses strong adaptive ability and robust character to the change of the missile＇ s inner parameters and disturbance of exterior environment. Finally, the simulation results are given to verify the validity of this method based on variable structure control with sliding mode.