Abstract—Fixed-time convergence control strategies based on adaptive Non-Singular Terminal Sliding Mode are proposed for rigid spacecraft attitude stabilization subject to actuator faults. A novel fixed-time sliding mode surface is used. Then, a fixed-time controller with adaptive law is derived to guarantee that the closed-loop system is stable in the sense of the fixed-time concept. Finally, the Lyapunov stability analysis shows that the controller has a good fault-tolerant performance on actuator faults. Numerical simulation verified the good performance of the controller in the attitude stabilization control.

Index Terms—Adaptive non-singular terminal sliding mode, attitude stabilization, fixed-time control, rigid spacecraft.

Zhiguo Han, Hui Fu, and Fanghao Tian are with School of Astronautics, Northwestern Polytechnical University, Shaanxi, Xi’an 710072, China.

Cite:Zhiguo Han, Hui Fu, Fanghao Tian, "Adaptive Fixed-Time Non-singular Terminal Sliding Mode Attitude Stabilization Control for Rigid Spacecraft with Actuator Faults," International Journal of Computer and Electrical Engineering vol. 11, no. 3, pp. 155-163, 2019.