Title :
Research on finite time control method based on terminal sliding mode for spacecraft attitude
Author :
Zheng Yan ; Cao Wei
Author_Institution :
Sch. of Inf. Sci. & Eng., Northeastern Univ., Shenyang, China
fDate :
May 31 2014-June 2 2014
Abstract :
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.
Keywords :
attitude control; control system synthesis; space vehicles; variable structure systems; control law design; dynamic equations; finite time control method; kinematic equations; nonsingular terminal sliding mode control algorithm; quaternion theory; spacecraft attitude; Attitude control; Educational institutions; Electronic mail; Kinematics; Mathematical model; Quaternions; Space vehicles; Attitude Control; Finite Time Control; Non-singular; Quaternion; Terminal Sliding Mode;
Conference_Titel :
Control and Decision Conference (2014 CCDC), The 26th Chinese
Conference_Location :
Changsha
Print_ISBN :
978-1-4799-3707-3
DOI :
10.1109/CCDC.2014.6852228
