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飞机侧向姿态运动的有关侧向力、力矩具有较强耦合性,且基于副翼、方向舵对侧向运动实施控制,侧向运动这些特点必然导致侧向控制系统设计的复杂性。为设计飞机偏航角侧向姿态控制系统,首先,基于飞机侧向运动的动力学方程组,建立了飞机侧向姿态控制系统全面运动结构图;然后,在分析全面运动结构图基础上,基于开环补偿原理,设计了一种飞机偏航角侧向姿态控制系统,即通过引入交叉传动比,将滚转通道的γ信号引入偏航通道,通过调节来实现基本协调转弯的控制结构方案;最后,在Matlab平台下,对所设计的飞机偏航角侧向姿态控制系统进行了大量仿真研究。仿真结果显示,通过调节可减弱飞机滚转运动和偏航运动的耦合影响,基于开环补偿的飞机偏航角侧向姿态控制系统是合理可行的。
The relative lateral force and moment with lateral attitude movement of the aircraft are strongly coupled. Based on the ailerons and the rudder, the lateral motion is controlled. The lateral motion will inevitably lead to the complexity of lateral control system design. In order to design the lateral yaw attitude control system of the aircraft, firstly, based on the dynamic equations of the lateral movement of the aircraft, a comprehensive motion structure chart of the lateral attitude control system of the aircraft is established. Based on the analysis of the comprehensive movement structure diagram, Open-loop compensation principle, an attitude control system of aircraft yaw angle is designed. That is to say, the γ signal of the roll passage is introduced into the yaw passage by introducing the cross gear ratio, and the control structure scheme of the basic coordinated turning is achieved through adjustment. Finally, a large number of simulation studies have been carried out on the designed attitude control system of aircraft yaw angle under Matlab platform. The simulation results show that the lateral yaw attitude control system based on open-loop compensation is reasonable and feasible by adjusting the coupling effect which can reduce the rolling motion and yawing of aircraft.