Authors: G. Vukovich; Y. Kim
Addresses: Lassonde School of Engineering, York University, Toronto, M3J 1P3, Canada ' Directorate of Engineering Development, Canadian Space Agency, 6767 route de l'aeroport, St. Hubert Quebec, J3Y 8Y9, Canada
Abstract: An approach is presented for using a steady state Kalman filter as a closed control loop controller and filter simultaneously. For a controllable/observable system with the same number of control inputs as states this output feedback controller simplifies control design by reducing the two step state estimator/controller design process to a single step. In application to a problem of regulating the separation of two low earth orbiting satellites it is shown that the Kalman filter controller provides good dynamic characteristics to the closed loop system as well as filtering capabilities.
Keywords: Kalman filter; output feedback control; controller design; LEO formation flying; spacecraft separation regulation; spacecraft orbit control; satellite formation flying; control design; low earth orbiting satellites; closed loop systems.
International Journal of Space Science and Engineering, 2015 Vol.3 No.2, pp.148 - 170
Received: 04 Jun 2015
Accepted: 06 Jul 2015
Published online: 09 Oct 2015 *