气动力/直接力复合控制导弹自动驾驶仪的鲁棒稳定性分析  

The Robustness and Stability Analysis for the Aerodynamic/Reaction-jet Controller of Missile Autopilot

作　　者：贾晓洪[1] 凡永华[1] 杨军[1] 

机构地区：[1]西北工业大学,西安710072

出　　处：《弹箭与制导学报》2005年第4期1-2,共2页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：航空科学基金(03D12004)

摘　　要：文中针对气动力/直接力复合控制导弹自动驾驶仪的前馈-反馈控制器结构特点,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,研究了气动力/直接力复合控制导弹自动驾驶仪的鲁棒稳定性问题,给出了采用气动力/直接力复合控制导弹自动驾仪的稳定域。The robustness and stability of an aerodynamic/reaction-jet multi-controller of missile autopilot is analyzed in the paper, which is base on the interpreting the corresponding relation between the blowing up coefficient of the reaction-jet device and the attack angle of the missile and the coupling principle of the autoeciousness channel which is caused by the reaction-jet control channel. Then the stable region of the missile autopilot has been worked out, which provides the evidence for the designing the reaction-jet device.

关 键 词：直接力/气动力复合控制 导弹 自动驾驶仪 鲁棒稳定性 

分 类 号：TJ765.1[兵器科学与技术—武器系统与运用工程]