含有耦合力矩对消装置的多体遥感卫星姿态控制  

Attitude control of multibody remote sensing satellite with coupled moment cancellation device

作　　者：张昊[1,2] 金磊[1,2] ZHANG Hao;JIN Lei(School of Astronautics,Beihang University,Beijing 100191,China;Key Laboratory of Spacecraft Design Optimization and Dynamic Simulation Technologies,Ministry of Education,Beijing 100191,China)

机构地区：[1]北京航空航天大学宇航学院,北京100191 [2]航天器设计优化与动态模拟技术教育部重点实验室,北京100191

出　　处：《飞行力学》2024年第5期55-63,共9页Flight Dynamics

摘　　要：含有多自由度光学载荷的遥感卫星可在卫星本体保持姿态稳定的情况下执行成像任务,对含有耦合力矩对消装置的多体遥感卫星姿态控制进行了研究。首先,基于显式凯恩方法建立了含有二自由度光学载荷的多体遥感卫星动力学模型;然后,建立了扩张状态观测器,对卫星本体受到的内外总扰动进行估计,并基于扩张状态观测器设计了星体姿态控制律;最后,设计了基于动量轮的内部耦合力矩对消方案,通过设计动量轮指令转速,利用动量轮产生的力矩抵消光学载荷转动对卫星本体产生的干扰力矩,避免了卫星本体姿态控制力矩幅值过大的问题。数值仿真验证了所建立的卫星动力学模型与控制方案的正确性和有效性。Remote sensing satellites with multiple degrees of freedom optical payload can perform imaging tasks while maintaining their attitudes stable.This paper investigates the attitude control of multibody remote sensing satellites with coupled moment cancellation devices.Firstly,a multibody remote sensing satellite dynamics model containing a 2-DOF optical payload is established based on the explicit Kane method.Then,an extended state observer is built to estimate the total internal and external disturbances suffered by the satellite body,and a satellite body attitude control law is de-signed based on the extended state observer.Finally,an internal coupled moment cancellation scheme based on momentum wheel is designed.By designing the command speed of the momentum wheel,the moment generated by the momentum wheel is used to offset the interference moment act-ing on the satellite body by the rotation of the optical payload,avoiding the problem of excessive am-plitude of the attitude control moment of the satellite body.The numerical simulation verifies the cor-rectness and effectiveness of the established satellite dynamics model and the control scheme.

关 键 词：多体卫星 凯恩方程 扩张状态观测器 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]