针对空空导弹的舵机卡死、驱动电路失效、伺服电机故障等单片舵失效的故障,设计了一种主动容错飞行控制系统,利用导弹尾舵中各舵面的内在联系和功能上的冗余,改变控制指令分配方式,实现弹体三通道稳定控制,仿真表明该方法对于典型的舵机失效问题具有较强的容错能力,提高了空空导弹飞行控制系统的可靠性。

An active fault-tolerant flight control system was designed in view of actuator deadlock, driver circuit failure, servo motor failure and other rudder faults of air-to-air missile. The inherent connection and functional redundancy among control surfaces of tail fin of missile were used and the distribution of control instruction was changed to achieve tri-channel autopilot stability design, simulation results indicate this method has strong fault-tolerant capability for typical actuator fault problems; the reliability of air-to-air missile control system is improved.