Spacecraft Momentum Management and Attitude Control Using a Receding Horizon Approach
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This paper presents the application of the Receding Horizon approach to the spacecraft momentum management problem. Attitude control of a satellite in a circular orbit under the influence of constant disturbances is considered. Control designs are demonstrated for a simplified planar case as well as for the full dynamics of the spacecraft. The response of the receding horizon controller is compared to a controller derived from Lyapunov conditions. The receding horizon approach demonstrates its ability to align the spacecraft to a torque equilibrium attitude and regulate the momentum of the control even when torque and rate constraints are included in the problem.
author list (cited authors)
Fisher, J., Bhattacharya, R., & Vadali, S.