Terminal Sliding Mode Control for Attitude Tracking of Spacecraft Based on Rotation Matrix

الملخص EN

Two finite-time controllers without unwinding for the attitude tracking control of the spacecraft are investigated based on the rotation matrix, in which a novel modified nonsingular fast terminal sliding manifold is developed to keep tr(R~)≠-1.

The first terminal sliding mode controller can compensate external disturbances with known bounds, while the second one can compensate external disturbances with unknown bounds by using an adaptive control method.

Since the first terminal sliding mode controller is continuous, it is able to avoid chattering phenomenon.

Theoretical analysis shows that both the two controllers can make spacecraft follow a time-varying reference attitude signal in finite time.

Numerical simulations also demonstrate that the proposed control schemes are effective.