The invention discloses a spacecraft control method and system considering residual vibration, and the method comprises the steps: constructing an Euler axis expression of a spacecraft attitude maneuver process based on the Euler rotation theorem; establishing a dynamic model of the flexible spacecraft; constructing a residual vibration expression of a flexible accessory in the flexible spacecraft; trajectory planning is carried out according to the characteristics of residual vibration and threshold limitation, and a spacecraft angular acceleration trajectory planning curve is generated; and forming a control loop according to the Euler axis expression of the spacecraft attitude maneuver process, the dynamic model of the flexible spacecraft and the spacecraft angular acceleration trajectory planning curve. The system comprises an Euler axis calculation module, a kinetic model construction module, a residual vibration construction module, an angular acceleration trajectory planning module and an overall control module. By using the invention, the vibration generated in the maneuvering process can be suppressed. The method can be widely applied to the field of spacecraft control.
本发明公开了一种考虑残余振动的航天器控制方法及系统,该方法包括:基于欧拉旋转定理,构建航天器姿态机动过程的欧拉轴表达式;建立挠性航天器的动力学模型;构建挠性航天器中的挠性附件的残余振动表达式;根据残余振动的特点和阈值限制进行轨迹规划,并生成航天器角加速度轨迹规划曲线;根据航天器姿态机动过程的欧拉轴表达式、挠性航天器的动力学模型以及航天器角加速度轨迹规划曲线,组成控制回路。该系统包括:欧拉轴计算模块、动力学模型构建模块、残余振动构建模块、角加速度轨迹规划模块和整体控制模块。通过使用本发明,能够抑制机动过程中产生的振动。本发明可广泛应用于航天器控制领域。
Spacecraft control method and system considering residual vibration
一种考虑残余振动的航天器控制方法及系统
2023-09-12
Patent
Electronic Resource
Chinese