BTT导弹变结构自适应控制仿真研究

Simulation of BTT Missile Based on Variable Structure Adaptive Control

一种变结构自适应控制律,可以不依赖于系统的精确数学模型,但对于BTT导弹气动参数不确定性具有良好的控制效果。采用Matlab,分别对BTT导弹滚转、偏航以及俯仰三个通道进行数值仿真,接着又对闭环系统进行了仿真验证,根据对仿真结果的分析,对该控制律进行了进一步的改进。所设计的改进控制律很好地解决了导弹数学模型不能精确获得以及参数大范围变化的问题,并且在很大程度上克服了导弹各通道间存在的耦合现象,与其它控制方法比较,具有算法相对简单,并且易于仿真验证的特点,对BTT导弹自动驾驶仪研究具有很好的指导意义。

A novel automatic pilot control law based on variable structure adaptive control, which is independent of the system＇ s precise math model, is adopted to solve the uncertainty of BTT missile aerodynamic parameters. The simulation software Matlab is adopted to simulate BTT missile＇ s roll, yaw, pitch channels and the closed loop system. Then necessary improvement is performed for solving the problems existing in the control system. The control law adopted in this thesis settles the problems that missile mathematic model can＇ t be obtained exactly and parameters change, and the coupling between channels is also overcome. The algorithm is simple and can be simulated easily.