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


  • 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.

name of conference

  • AIAA Guidance, Navigation and Control Conference and Exhibit

published proceedings

  • AIAA Guidance, Navigation and Control Conference and Exhibit

author list (cited authors)

  • Fisher, J., Bhattacharya, R., & Vadali, S.

citation count

  • 4

complete list of authors

  • Fisher, James||Bhattacharya, Raktim||Vadali, Srinivas

publication date

  • August 2007