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由于防/除冰系统总会出现故障或者除冰不彻底,因此仅依靠防/除冰系统实现结冰条件下的安全飞行并非完全可靠,研究结冰后飞机控制律重构对飞机操纵安全和飞行安全极其重要。针对飞机的纵向运动建立了结冰影响模型和纵向动力学模型,采用鲁棒伺服线性二次型调节器(LQR)最优控制设计了飞机结冰后空中飞行纵向控制律,模拟了飞机在俯仰姿态保持模式下遭遇不同严重程度结冰后的动态响应特性,并与常规PID控制进行对比。结果表明,所设计的控制律能够有效改善结冰飞机的飞行性能和飞行品质,准确跟踪给定的俯仰角指令,且抗干扰能力、动态性能以及鲁棒性均优于常规PID控制。为飞机结冰后的重构控制问题和自动飞行控制,提供了新的思路。
Since the anti-deicing system always fails or the de-icing is not complete, it is not completely reliable to rely on the anti-deicing system to achieve safe flight under icing conditions. After the icing, the control law reconstructs the aircraft control safety and Flight safety is extremely important. The icing influence model and the longitudinal dynamics model are established for the longitudinal movement of the aircraft. The LQR optimal control is used to design the longitudinal control law of the airborne icing after flight, The dynamic response under different conditions of icing in the attitude retention mode was compared with the conventional PID control. The results show that the proposed control law can effectively improve the flight performance and flight quality of icing aircraft and accurately track the given pitch angle command. And the anti-interference ability, dynamic performance and robustness are better than the conventional PID control. It provides a new idea for the reconstruction control problem and automatic flight control after the icing.