Abstract The Linear Quadratic Regulator (LQR) control design method has been widely used for satellite formation maintenance. In this paper a new feedback control is proposed to solve LQR problems using the state transition matrix. Such a method has the potential to reduce the online computational burden. We apply the control law to formation flying maintenance under J 2 perturbation using the Gim-Alfriend state transition matrix. The numerical simulations demonstrate the STM feedback control via receding horizon scheme works well. The projected circular orbits are maintained very well for the circular and elliptic Chief orbits after 100 day propagation under J 2 influence. Much control effort is needed to track the projected circular orbits if the Chief orbit is elliptic.
Feedback Control for Formation Flying Maintenance Using State Transition Matrix
The Journal of the Astronautical Sciences ; 59 , 1 ; 177-192
2012-06-01
16 pages
Article (Journal)
Electronic Resource
English
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