Spacecraft Momentum Management and Attitude Control Using a Receding Horizon Approach Conference Paper uri icon

abstract

  • 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.

citation count

  • 3

publication date

  • June 2007