Attitude tracking control of on-orbit-servicing spacecraft based on eigenaxis maneuver

被引：0

作者：

Wang, Feng ^{[1
]}

Cao, Xi-Bin ^{[1
]}

Zhang, Shi-Jie ^{[1
]}

机构：

[1] Research Center of Satellite Technology, Harbin Institute of Technology, Harbin 150001, China

来源：

Yuhang Xuebao/Journal of Astronautics | 2008年 / 29卷 / 02期

关键词：

Rotation; -; Navigation;

D O I：

暂无

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

An eigenaxis tracking control algorithm is presented to provide rapid attitude tracking and synchronized rotation for on-orbit-servicing spacecraft. Based on the relative motion error dynamic equation and the similar strategy applied in move-to-rest attitude maneuver, the algorithm imported a parameter, which was used to describe the deviation degree related to eigenaxis, as a feedback to ensure that whole tracking is an eigenaxis rotation. Finally, It carries out the simulation, which indicates that smooth maneuver process, high tracking error, short tracking path and nearly optimal time are achieved after the whole tracking.

引用

页码：570 / 575