结构受损飞机动力学模型与飞行控制方法

Dynamic model and flight control method for structure damaged aircraft

为实现对结构部分受损飞机的安全控制,建立了其动力学模型,通过分析将结构受损飞机的旋转运动分解为正常飞机旋转运动和由于受损引起的扰动运动,将结构受损飞机的控制转化为对扰动等不确定性因素的抑制问题.提出了一种基于扩张状态观测器的轨迹线性化控制方法进行飞行控制律设计,使系统具有较强的鲁棒性.仿真结果表明:当飞机右侧机翼缺损15%半翼展长时,控制系统能实现结构受损飞机的解耦控制,角速度响应能较好地跟踪指令,有效抑制了结构受损带来的不确定性和扰动.

The dynamic model of a structure damaged aircraft was presented,for designing flight control law to ensure flight safety when the aircraft structure damaged partially.After analyzing the dynamic model,the rotational motion of structure damaged aircraft could be decomposed to normal aircraft rotational motion and disturbance motion by structural damage.The control of structure damaged aircraft could be translated to suppress the disturbance motion and uncertainties.A trajectory linearization control method based on extended state observer was proposed to design the robust flight control law.The simulation results indicate that,the flight control system can achieve the decouple control of the aircraft when the right wing lost 15%.And the attitude rate response follows the command well.The control system can endure the uncertainties and disturbance because of structure damage.