Fixed-Time Attitude Control for Rigid Spacecraft With Actuator Saturation and Faults

• Published in: IEEE transactions on control systems technology Vol. 24; no. 5; pp. 1892 - 1898
• Main Authors: Boyan Jiang, Qinglei Hu, Friswell, Michael I.
• Format: Journal Article
• Language: English
• Published: New York IEEE 01.09.2016; The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
• Subjects: Actuator faults; Actuators; Attitude control; Controllers; Convergence; Disturbances; Fault tolerance; Fault tolerant systems; Faults; fixed-time control; input saturation; Mathematical analysis; Saturation; Space vehicles; Spacecraft; Spacecraft performance; Symmetric matrices
• ISSN: 1063-6536; 1558-0865
• DOI: 10.1109/TCST.2016.2519838

This brief 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.