Research on finite time control method based on terminal sliding mode for spacecraft attitude

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.