Fixed-time Attitude Control for Rigid Spacecraft with Actuator Saturation and Faults
B Jiang (Harbin Institute of Technology, China), QL Hu (Beihang University, China) & MI Friswell (Swansea University)
IEEE Transactions on Control Systems Technology, Vol. 24, No. 5, September 2016, pp. 1892-1898
This paper investigates the finite time control problem associated with attitude stabilization of a rigid spacecraft subject to external disturbance, actuator faults and input saturation. More specifically, a novel fixed-time sliding mode surface is developed, and the settling time of the defined surface is shown to be independent of the initial conditions of the system. Then, a finite time controller is derived to guarantee that the closed-loop system is stable in the sense of the fixed-time concept. The actuator-magnitude constraints are rigorously enforced and the attitude of the rigid spacecraft converges to the equilibrium in a finite time even in the presence of external disturbances and actuator faults. Numerical simulations illustrate the spacecraft performance obtained using the proposed controller.
This material has been published in the IEEE Transactions on Control Systems Technology, Vol. 24, No. 5, September 2016, pp. 1892-1898, the only definitive repository of the content that has been certified and accepted after peer review. Copyright and all rights therein are retained by IEEE.
Link to paper using doi: 10.1109/TCST.2016.2519838
IEEE Transactions on Control Systems Technology