Reasearch on Finite time Control Method Based on Terminal Sliding Mode for Spacecraft Attitude

被引：0

作者：

Zheng Yan ^{[1
]}

Cao Wei ^{[1
]}

机构：

[1] Northeastern Univ, Sch Informat Sci & Engn, Shenyang 110819, Peoples R China

来源：

26TH CHINESE CONTROL AND DECISION CONFERENCE (2014 CCDC) | 2014年

关键词：

Attitude Control; Terminal Sliding Mode; Finite Time Control; Non-singular; Quaternion; VARIABLE-STRUCTURE CONTROL;

D O I：

暂无

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

The quaternion theory is used to describe the attitude of spacecraft based on the analysis for several typical description methods of kinematic and dynamic equations and the system model for the attitude of spacecraft is built. The control law design for spacecraft attitude based on non-singular terminal sliding mode control algorithm is proposed using the coupling between kinematic and dynamic equations. Then it is proved that the attitude of spacecraft can converge to the target posture in finite time by finite time control theory. The simulation results approve that control law design is feasible.

引用

页码：555 / 558

页数：4

共 10 条

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