大攻角飞行导弹自动驾驶仪反馈线性化设计

The Design for Autopilot of Large Attack Angle Missile by Using Feedback Linearization Method

针对大攻角空空导弹飞行过程中复杂的非线性空气动力学特性,提出了采用反馈线性化进行控制器设计的方法。在完成导弹俯仰通道的非线性建模的基础上,采用反馈线性化理论对导弹模型进行精确线性化,然后,对线性化后的系统给出了变结构控制系统设计。最后,通过仿真验证了所设计的控制器具有良好的动态性能及较好的工程参考价值。

Based on the characteristics of the complicated aerodynamics for the large attack angle airto-air missile, using feedback linearization approach for the design of the flight control systero is proposed. In the first part of this paper, the nonlinear model of the pitch channel is given, then accurately linearizes the model with the feedback linearity theory, finally designs the flight control system using variable structure control with sliding mode. It is proved by simulation that the control system appears good dynamical performance and has a better value for engineering reference.