The invention discloses a double-vibration-suppression active-disturbance-rejection flexible spacecraft attitude control method based on shaping planning, and particularly relates to the technical field of spacecraft attitude control, which comprises the following steps: on the basis of an existing all-wheel-drive system theoretical framework, according to flexible spacecraft attitude dynamics and kinematics models, determining the attitude of a flexible spacecraft; converting the spacecraft attitude model into an all-drive system control model; designing an attitude controller architecture for the all-wheel-drive system control model; for a linear feedback part of the control law, a parameter matrix is determined by a direct parameter method under an all-drive system theoretical framework; performing comprehensive observation and estimation on a nonlinear term compensation part of the control law by adopting an extended state observer; and for the target attitude, the target attitude is designed by adopting path planning and input molding, so that the flexible vibration is effectively inhibited to realize high-precision agile attitude control while rapid attitude control is ensured.
本发明公开了基于整形规划的双抑振自抗扰挠性航天器姿态控制方法,具体涉及航天器姿态控制技术领域,包括如下步骤:基于现有的全驱系统理论框架,根据挠性航天器姿态动力学与运动学模型,将航天器姿态模型转换为全驱系统控制模型;针对全驱系统控制模型设计姿态控制器架构;对于控制律的线性反馈部分,其参数矩阵由全驱系统理论框架下的直接参数法确定;对于控制律的非线性项补偿部分,采用扩张状态观测器对其进行综合观测估计;对于目标姿态,采用路径规划与输入成型对其进行设计,以保证快速姿态控制的同时,挠性振动得以有效抑制以实现高精度敏捷姿态控制。
Double-vibration-suppression active-disturbance-rejection flexible spacecraft attitude control method based on shaping programming
基于整形规划的双抑振自抗扰挠性航天器姿态控制方法
2024-11-08
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
Active Vibration Suppression in Flexible Spacecraft Attitude Tracking
Online Contents | 1998
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