Attitude Tracking Control of On-Orbit-Servicing Spacecraft Based on Eigenaxis Maneuver

摘要：

An eigenaxis tracking control algorithm is present ed to provide rapid attitude tracking and synchronized rot ation for on-orbit-servicing spacecraft. Based on the relati ve motion error dynamic equation, the algorithm uses the s trategy similar with the move-to-rest attitude maneuver an d imports a parameter describing the deviation degree fro m eigenaxis as feedback to ensure the whole tracking is an eigenaxis rotation. Finally, It carries out the simulation. A nd the results indicate the smooth maneuver process, high error accuracy, short tracking path and near optimal time are achieved after the whole tracking.

作者: Feng WANG Xue-qin CHEN Xi-bin CAO

作者单位: Research Center of Satellite Technology,Harbin Institute of Technology,China

会议类型: 国际会议

会议名称: The 2nd International Symposium on Systems and Control in Aeronautics and Astronautics(第二届航空航天系统与控制国际会议 ISSCAA 2008)

会议地点: 深圳

会议语种:英文

页码: 811-815

在线出版日期: 2008-12-10（万方平台首次上网日期，不代表论文的发表时间）