空间控制技术与应用2024，Vol.50Issue(4)：45-54,10.DOI:10.3969/j.issn.1674-1579.2024.04.006
偏心航天器有限推力姿轨耦合控制
Integrated Orbit and Attitude Control of Spacecraft with Deviated Centroid and Finite Thrust
摘要
Abstract
A finite thrust orbit and attitude control scheme is proposed to solve the problem of unadjustable orbit control thrust with large misalignment for a spacecraft with deviated centroid.The proposed orbit control scheme can control multiple orbit elements at the same time.The problem of unadjustable orbit control thrust is solved by taking the thrust angle as the control input of orbit control.When designing the attitude control strategy to track the de-sired attitude of orbit control,the large interference torque caused by the thrust misalignment is considered.To solve the problem of large disturbance,the traditional asymptotically stable attitude control law is improved.The coupling relationship of three-axis attitude is used to counteract the influence of interference torque.The effective-ness of the orbit and attitude control strategy is verified by numerical simulation.关键词
姿轨耦合/有限推力/推力偏心/姿态跟踪Key words
integrated orbit and attitude/finite thrust/thrust misalignment/attitude tracking分类
航空航天引用本文复制引用
刘江,贾英宏..偏心航天器有限推力姿轨耦合控制[J].空间控制技术与应用,2024,50(4):45-54,10.基金项目
国家自然科学基金资助项目(11772023) Supported by National Natural Science Foundation of China(11772023) （11772023）
