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在飞机飞行过程中,通过对天线控制单元的控制,完成方位、俯仰以及直线运动,保证天线阵面能够始终实时地完成对星,以建立稳定的数据传输链路,实现高质量的通讯。由于单元本身结构的复杂性,以及工作环境的多变性,迫切要求一种能对系统参数摄动和外部扰动具有强鲁棒性的控制器来实现对飞行器姿态的控制。具有强鲁棒性和强抗干扰能力的滑模变结构控制易引起系统的抖振,为消除并避免激励系统中未用模型所表示的高频成分,提出采用变指数趋近律的滑模变结构控制策略。将天线阵面的Adams模型和电机滑模控制器的Simulink模型进行联合仿真,并比较方位电机和俯仰电机分别在滑模变结构控制和PI控制下得到的不同结果。得到结论,滑模变结构控制使精度要求高的天线伺服单元能够快速响应,提高了系统的鲁棒性以及抗干扰能力。相较于PI控制具有更好的性能。
Through the control of the antenna control unit during the aircraft flight, the azimuth, pitch and linear motion are completed to ensure that the antenna array can always finish the satellite in real time so as to establish a stable data transmission link and achieve high-quality communications. Due to the complexity of the unit itself and the variability of the working environment, it is urgently required to control the attitude of the aircraft with a controller that is robust to system parameter perturbations and external perturbations. The sliding mode variable structure control with strong robustness and strong anti-jamming ability easily causes chattering of the system. In order to eliminate and avoid the high-frequency components represented by unused models in the excitation system, a sliding mode using a variable exponential approach law Variable structure control strategy. The Adams model of the antenna array and the Simulink model of the motor sliding mode controller are co-simulated, and the different results obtained by the sliding mode variable structure control and the PI control by the azimuth motor and the pitching motor are compared respectively. It is concluded that the sliding mode variable structure control can make the antenna servo unit with high accuracy requirements respond quickly and improve the system robustness and anti-interference ability. It has better performance than PI control.