A sliding mode controller is proposed for the attitude control of spacecraft reorientation with attitude constraints. By introducing a potential function, a novel sliding function is designed. With the structure of the proposed sliding function, uniqueness of the equilibrium and fixed-time convergence are rigorously proven. Another advantage of the proposed controller is that the feasibility of attitude constraints can be proven not only on the sliding surface but also outside it. Moreover, the singularity issue of the proposed controller is resolved. Effectiveness of the proposed method is demonstrated by carrying out two numerical simulation.

This paper addresses the event-triggered attitude control problem for spacecraft anti-unwinding reorientation with multiple attitude constraints in the presence of external disturbance. Based on a designed novel potential function(PF), a new sliding mode controller is proposed to guarantee the completeness of anti-unwinding reorientation with multiple attitude constraints and external disturbance. Different from existing continuous attitude reorientation controller, the static and dynamic event-triggered mechanisms, related with the sliding mode variable and disturbance bound, are then constructed. With the designed event-triggered sliding mode control schemes, the attitude system asymptotic stability, the satisfaction of attitude constraints with anti-unwinding action and free of Zeno phenomenon despite on external disturbance are proved theoretically. Numerical simulations results confirm that the proposed methods can significantly reduce resource usage while guaranteeing the desired performance.

This article addresses the problem of spacecraft reorientation subject to attitude pointing, angular velocity, and actuator constraints. In order to tackle the attitude pointing constraints, a potential function is proposed, which is parameterized to allow for a wider range of optimal repointing solutions with attitude pointing constraints. Based on the potential function, a feedback control law is then designed for ensuring the system stability. The controller gains are optimized using a gradient-based optimal parameter tuning method. Furthermore, by imposing the angular velocity constraints and the actuator constraints into the formulation, the optimal parameter tuning method also ensures the satisfaction of these constraints. Therefore, stability, optimality, and feasibility are achieved simultaneously. Numerical simulations demonstrate accurate repointing maneuvering under different types of constraints.