基于滑模控制的导弹制导系统设计

Design of Missile Guidance System Based on Sliding Curve Method

摘要:

对传统的导弹制导系统进行改进设计，改善导弹的路径跟踪效果。首先引入Dubins曲线对导弹进行航迹规划进行，并基于滑模控制进行导弹制导策略的设计，自动驾驶仪系统采用级联比例积分控制器。Dubins曲线能为导弹创建更平滑的参考轨迹，减少导弹的超冲运动与振荡现象。滑模控制通过计算导弹与参考轨迹的相对距离，获得参考方位角，进而实现对参考轨迹的跟踪，能够提高制导系统响应速度、抗干扰能力。对导弹跟踪路径效果进行仿真，对比引入dubins曲线前后导弹的跟踪轨迹的误差与振荡现象，证明了引入dubins曲线对于导弹的路径规划工作具有显著帮助，并对结果中的一些现象进行了讨论。并已dubins曲线作为仿真路径，对传统比例制导策略和改进型滑模控制制导策略的仿真结果进行对比，证明了改进型制导系统设计的可行性，并对其路径跟踪表现的特点进行了讨论。

Abstract:

The traditional missile guidance system is improved and designed to improve the missile's path tracking effect. Firstly, the Dubins curve is introduced to plan the missile's trajectory, and the missile guidance strategy is designed based on sliding mode control. The autopilot system adopts the cascade proportional integral controller. The Dubins curve can create a smoother reference trajectory for the missile, reducing the overshoot and oscillation of the missile. Sliding mode control obtains the reference azimuth by calculating the relative distance between the missile and the reference trajectory, and then realizes the tracking of the reference trajectory, which can improve the response speed and anti-interference ability of the guidance system. The effect of missile tracking path is simulated, and the error and oscillation of the missile's tracking trajectory before and after the introduction of the dubins curve is compared. The dubins curve is used as the simulation path, and the simulation results of the traditional proportional guidance strategy and the improved sliding mode control guidance strategy are compared, which proves the feasibility of the improved guidance system design, and discusses the characteristics of its path tracking performance.