一种气动力/直接力复合控制导弹自动驾驶仪设计

文中提出了一种气动力／直接力复合控制导弹自动驾驶仪的前馈一反馈控制器结构．通过攻角反馈自动驾驶仪以及直接力反馈主控回路控制器设计，解决了传统法向过载误差控制器中气动力与直接力两个控制回路由于使用同一个加速度传感器所带来的复合控制系统的解耦同题。文中给出了攻角反馈自动驾驶仪和直接力主控回路的设计方法。通过数字仿真，验证了所设计的直接力／气动力复合控制器可以有效提高导弹末端对付高机动目标的快速响应能力。

The Design of Aerodynamic/Reaction-jet Controller of Missile Autopilot

A new multi-controller structure of missile autopilot is presented. This multi-controller includes an aerodynamic autopilot which uses attack angle as a feedback parameter in the feedforward channel and a mail control channel which uses reaction-jet device. The problem of coupling of traditional multi-controller using one acceleration sensor in aerodynamic and reaction-jet control channels is well solved. The method of designing reaction-jet mail control channel and autopilot which uses attack angle as feedback parameter is demonstrated, and the result that application of aerodynamic/reaction-jet muhi-controller can greatly enhance response speed and maneuverability of the missile is proved by simulation.