大攻角导弹法向过载控制的变结构设计

通过分析大攻角导弹在飞行过程中出现的问题和滑模变结构理论所具有的优势,本文针对法向过载控制进行优化设计,目的是使其对内在参数变化等因素有较强的适应能力和鲁棒性。基于"过载+角速度+角度"三回路自动驾驶仪,将气动参数的变化等效为动力参数的摄动,设计变结构控制器,重构法向过载微分信号,易于工程实现。通过仿真验证了变结构控制器的性能,结果表明在大攻角飞行条件下,导弹法向过载变结构自动驾驶仪抗模型参数摄动的鲁棒性方面优于传统设计方法。

Design of VSC for Overload Control in High Angle-of-attack Missile

The purpose of this paper is to study the overload control system of the high angle-of-attack missile. First, the prob- lems of the high angle-of-attack missile in flight process and the advantages of the variable structure control theory are analyzed. Then, the nonlinear variation of aerodynamic parameters are treated as bound-limited movement of linear parameters. Based on the accelerometer flight control system, the sliding mode controller and the control law are designed. The performance of the con- troller is test under parameter perturbation in Simnlink. The result shows that the variable structure autopilot of overload is superi- or to the traditional design under the condition of the high angle-of-attack flight.