飞机纵向运动自修复控制律设计

Self-repairing control law design of aircraft longitudinal maneuver

为使飞机在舵面故障时仍能稳定操纵,设计了一种纵向运动自适应控制律。采用链式力矩分配策略将因平尾损伤而损失的控制力矩分配到推力矢量舵面,重构舵面控制和控制器参数自适应调节。仿真结果表明:当舵面正常时,由于控制器本身的鲁棒性,控制参数调整很小即可获得非常好的控制效果;当舵面损失超过80%时,采用自适应控制律进行参数调整后误差振荡减少、超调很小,获得了良好的控制效果。

In order to stably control the aircraft in case of tail actuator failure, an adaptive control law of longitudinal maneuver was prompted. Actuator configuration and controller parameter＇ s adaptive control with nonlinear function was used in the self-repairing control law design. The simulation results show that a good control performance can be achieved with small control parameter adjustment and proper operation of the actuator due to the robutness of the controller itself. However, when the actuator is 80% damaged, the control performance is improved apparently, error oscillates slightly and overshoot becomes small by using adaptive control law for parameter adjustment.