基于变结构控制的卫星姿态轨道一体化控制方法

针对导航卫星四斜装化学推进姿态轨道一体化控制系统,设计了两级脉冲的变结构相平面分区的姿态控制器.本文建立了相平面控制器的模型,给出了时频域下参数变化趋势的稳定性分析.创造性地将该控制系统建立为变结构控制模型,根据现代控制理论给出了系统得以稳定条件下的参数下界.通过控制器参数设计,有效地降低了开关线处的震颤,保证了控制系统的稳定,提高了轨道控制效率,并就挠性卫星推力器在最恶劣的安装偏差情况下进行了数学仿真.最终,通过卫星在轨姿态控制良好的表现,充分验证了姿态控制算法设计的正确性、有效性和鲁棒性.

The satellite integrated attitude-orbit control method based on variable structure control

Herein,we design an attitude control method that used in the orbit maneuver mode.In the designed method,four inclinefixed thrusters with chemical propulsion are required to simultaneously perform orbit and attitude control.Although this is convenient,it causes attitude disturbance.This study aims to develop a simple and robust attitude control method to address this situation.Therefore,we design a two-class pulse width’s phase plane attitude controller.We construct a dynamic model for the variable structure controller,and analyze the stability under various time-frequency field parameter values.We use the sliding mode and modern control theory to determine the lower bound of the parameter.The controller can decrease the chattering of the switching line,as well as guarantee the stability of the system.Then,we simulate the most severe fix error under flexible conditions.We also verify the correctness,effectiveness,and robustness of the proposed method based on the excellent performance of satellites on orbit.