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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.
In order to realize the safety control of partially damaged aircraft, a dynamic model is established. By analyzing the rotation of the damaged aircraft is decomposed into the normal rotation of the aircraft and the disturbance movement caused by the damage, the structure of the damaged aircraft Control into the suppression of uncertain factors such as disturbance.A trajectory linearization control method based on the extended state observer is proposed to design the flight control law so that the system has strong robustness.The simulation results show that when The control system can achieve the decoupling control of the structurally damaged aircraft when the right wing of the aircraft has a 15% half-span defect and the angular velocity response can better follow the command, effectively suppressing the structural uncertainties and disturbances caused by structural damage .