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实现快速、精准、抗扰动性强的倾斜姿态控制,是大型客机自动着陆控制系统设计的关键技术之一。以Boeing707飞机在常值侧风扰动下的非线性数学模型为基础,通过配平线性化得到线性方程,综合设计了进近着陆阶段的姿态控制律。由于使用PID控制方法的滚转角响应难以兼顾快速性与稳态性能,设计了基于鲁棒H∞理论的倾斜姿态控制律。分别对两种控制方法跟踪滚转角阶跃指令,以及抗侧风扰动的控制效果进行了比较分析。仿真结果表明,状态反馈H∞控制方法能够实现快速、精准、无超调的倾斜姿态控制,且有侧风扰动存在时具有快速的恢复能力、较好的乘坐品质和较大的抗扰动控制余度。
It is one of the key technologies to design the automatic landing control system for large-scale passenger aircraft, which can realize the tilt attitude control which is fast, accurate and anti-disturbance. Based on the nonlinear mathematical model of Boeing707 under constant-value side-wind disturbance, the linear equations are obtained through the leveling linearization, and the attitude control law of the approach landing stage is designed. Because the roll angle response using PID control method is difficult to balance the fastness and steady-state performance, a tilt attitude control law based on robust H∞ theory is designed. The control methods of tracking roll angle step command and anti-crosswind disturbance are compared and analyzed respectively. The simulation results show that the state feedback H∞ control method can achieve fast, precise and non-overshooting tilt attitude control with rapid recovery ability in the presence of crosswind disturbance, better riding quality and greater anti-disturbance control degree.