基于模糊逻辑的航天器信息融合预见姿态控制

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中图分类号：0313；V448.22 文献标志码：A 文章编号：1000-4939（2025）06-1246-08

Abstract：Large flexible appendages of flexible spacecraft are characterised by their large scale and low stifess，resulting in vibration of large flexible appendages that canseriously affect the atitude precision of the spacecraft. Information fusion preview control is combined with fuzzy control to construct the attitude controller. According to the information fusion theory，the spacecraft's desired trajectory and system dynamics information are fused，the optimal preview control law is derived. The optimal preview control law can be easily obtained due to the information fusion control has a simple design process and low computational burden. In real engineering，the control torque generated by the actuator is limited.The fuzzy controllr is employed to adjust the parameters of the control lawon-line in order to satisfy the requirements of limitation.Simulation results show that the designed control strategy with high control performance can effctively suppress the vibration of the flexible appendages，and the atitude angle can reach the desired value accurately and quickly. The proposed control strategy can be served as a reference for the engineering application oflarge flexible spacecraft attitude control.

Key words：large flexible spacecraft;； atitude control; information fusion； preview control; fuzzy logic

为了使现代航天器具有完成各种高难度空间任务的复杂功能[]，航天器通常搭载了多种挠性附件。（剩余13473字）