Fixed-time fault-tolerant control of spacecraft based on adaptive non-singular terminal sliding mode

Fixed-time fault-tolerant control (FTC) problem for spacecraft is investigated, in the disturbances,actuator failures and inertial uncertainties. An adaptive non-singular terminal sliding mode control method is derived to ensure closed-loop system stability in the fixed-time sense. Specifically, a novel fixed-time double-power terminal sliding mode surface is presented to strike a balance between the quick response and the small overshoot. Numerical simulations show that the scheme has low control input, small overshoot and good tracking performance during control processes with actuator failures.