Finite-time Attitude Control of Spacecraft

摘要：

In this paper, we propose two .nite-time control laws for rigid spacecraft. We use quaternion for attitude representation and employ the Lagrange-like model for convenience of system design. First, by using the .nite-time control method, a full-state feedback control scheme is presented. Then, considering no angular velocity measurement can be obtained, we propose a .nite-time control law. Under the proposed control laws, the attitude of spacecraft converge to desired attitude in .nite time.

关键词： Finite Time Converge Attitude Control State Feedback Output Feedback

作者: Dai Gao Siming Meng Wei Yao Jianting Lv

作者单位: School of Astronautics , Harbin Institute of Technology, Harbin 150080, P.R.China School of MathematicalScience, Heilongjiang University, Harbin 150080, P.R.China School of Mathematical Science, Heilongjiang University, Harbin 150080, P.R.China

会议类型: 国际会议

会议名称: The 24th Chinese Control and Decision Conference (第24届中国控制与决策学术年会 2012 CCDC)

会议地点: 太原

会议语种:英文

页码: 1409-1413

在线出版日期: 2012-05-23（万方平台首次上网日期，不代表论文的发表时间）