Constrained Feedback Control for Spacecraft Reorientation With an Optimal Gain

Abstract

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.