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为了确保飞机在变后掠角过程中的飞行稳定性,提出了一种基于滚动时域优化(Receding horizon optimal,RHO)的修正控制方法。首先,采用反步方法进行标称控制律设计,提供基本的飞行稳定性和跟踪性能。其次,将指令滤波器表示成状态空间的形式,基于指令滤波器、飞机和积分跟踪误差的状态方程得到一个增广状态方程。然后,采用RHO方法进行修正控制律设计,在有限滚动时域内计算得到修正控制量,对标称控制器输出进行在线补偿,确保快速变后掠角过程中的飞行稳定性。最后,通过变后掠角飞机航迹倾斜角控制系统仿真对算法的有效性进行了验证。
In order to ensure the flight stability of aircraft during variable sweep angle, a modified control method based on RHO (roll horizon optimization) is proposed. First, a backstepping approach is used to design the nominal control law to provide basic flight stability and tracking performance. Secondly, the instruction filter is expressed in the form of state space, and an augmented state equation is obtained based on the state equations of the command filter, aircraft and integral tracking error. Then, the modified control law is designed by using RHO method, the corrected control quantity is calculated in the finite rolling time domain, and the output of the nominal controller is compensated online to ensure the flight stability during the rapid variable sweep. Finally, the validity of the algorithm is verified through the system simulation of aircraft flight path tilt angle control.