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针对低轨卫星由于气动干扰力矩较大导致偏置动量控制精度较低的问题,理论分析了气动干扰力矩并进行建模,讨论了基于角动量与角速率作用产生陀螺力矩的影响。固定偏置动量卫星X、Z轴基于磁力矩器控制,气动干扰力矩严重时又处于磁不可控区,为确保姿态控制精度,考虑增加1台反作用飞轮抑制气动干扰力矩,反作用飞轮可与偏置动量轮组成单自由度偏置动量控制,反作用飞轮用作补偿轮,沿X轴安装。采用飞轮角动量补偿和磁补偿方法提高固定偏置动量控制精度:为防止赤道上空X轴处于磁不可控区时补偿轮角动量变化对X轴的干扰,对补偿轮角动量输出进行限幅,给出了补偿算法;为防止反作用飞轮限幅后角动量对Z轴产生干扰,设计了磁补偿控制策略。仿真结果表明:在同时采用角动量补偿和磁补偿后三轴姿态控制精度0.2°,较无补偿时有大幅提高。
Aiming at the problem that the precision of the bias momentum control is low due to the larger aerodynamic disturbance torque, the aerodynamic interference torque is analyzed theoretically and modeled, and the influence of the gyroscopic moment generated by the angular momentum and angular velocity is discussed. Fixed-offset momentum satellite X, Z axis is based on the magnetic torque control, the aerodynamic disturbance torque is serious in the magnetic uncontrollable area, in order to ensure the attitude control accuracy, consider adding a reactive flywheel to suppress aerodynamic interference torque, the reaction flywheel can be offset The momentum wheel consists of a single-degree-of-freedom offset momentum control and the reaction flywheel is used as a compensating wheel mounted along the X-axis. Adopting the methods of flywheel angular momentum compensation and magnetic compensation to improve the control precision of fixed offset momentum: In order to prevent the X-axis interference of the angular fluctuation of the wheel from compensating the X-axis when the X-axis is in the uncontrollable area over the equator, The compensation algorithm is given. To prevent the angular momentum of the reactive flywheel from interfering with the Z axis, the magnetic compensation control strategy is designed. The simulation results show that the accuracy of three-axis attitude control with angular momentum compensation and magnetic compensation is improved by 0.2 °, which is higher than that without compensation.