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针对对地观测敏捷卫星大角度快速机动、高控制精度的任务需求,提出了联合推力器与飞轮作为执行机构的控制策略。该控制策略综合利用2种执行机构的优点:推力器以前馈的形式提供机动过程中所需的主要力矩以实现航天器大角度的快速机动,而飞轮以反馈的形式提供精准的控制力矩以提高机动过程中的姿态控制精度。为补偿由于初始状态偏差和推力器输出力矩不准确所带来的控制误差,采用变结构控制设计了2种姿态跟踪控制器,使航天器能够渐进地跟踪上参考轨迹。并对姿态机动控制过程中,飞轮力矩及转速可能出现的饱和问题作了相应的修正。仿真结果表明了所提控制策略及所设计控制算法的可行性和有效性。
Aiming at the mission requirements of agile satellite with large angle and fast maneuvering and high control precision, a control strategy of joint thruster and flywheel as actuator is proposed. The control strategy combines the advantages of two actuators: the thrusters provide the main moments required in the maneuver in the form of feedforward to achieve high-speed maneuvering of the spacecraft, while the flywheel provides precise control torque in the form of feedback to improve Attitude control accuracy during maneuvering. In order to compensate for the control error caused by inaccurate initial state deviation and thruster output torque, two kinds of attitude tracking controllers are designed with variable structure control so that the spacecraft can track the reference trajectory gradually. In the process of attitude maneuver control, the saturation problems of flywheel torque and speed may be corrected accordingly. The simulation results show that the proposed control strategy and the designed control algorithm are feasible and effective.