基于前馈—反馈控制导弹自动驾驶仪鲁棒稳定性分析

Robustness and Stability Analysis for the Feedforward-Feedback Multiple Controller of Missile Autopilot

针对一类前馈—反馈的气动力/直接力复合控制导弹自动驾驶仪结构特点,基于对直接力喷流装置放大因子与攻角的对应关系和直接力寄生回路的耦合机理的分析,完成了气动力/直接力复合控制系统的非线性建模,并采用Lyapunov非线性稳定性理论,对复合控制导弹自动驾驶仪的鲁棒稳定性问题进行了证明,给出了采用气动力/直接力复合控制导弹自动驾驶仪的稳定域,具有较好的工程参考价值。

The robustness and stability analysis for a feedforward-- feedback Aerodynamic/Reaction--jet multi--controller of missile autopilot is present in the paper, which is base on the interpreting the nonlinear coupled relation between the blowing up coefficient of the reac- tion-jet device and the attack angle of the missile which is caused by the Reaction--jet control channel. First a nonlinear model of the multi --controller is given. Then the robust problem has been proved by using Lyapunov theorem and the stable region of the missile autopilot has been worked out, which provides the evidence for the designing the reaction--jet device.