Stationkeeping manoeuvres for geostationary satellites using feedback control techniques

In this paper we discuss the determination of the correction manoeuvres required to control geostationary satellites within a predefined space box over a place above the Earth using a feedback control technique. The control algorithm formulated here combines an accurate numerical propagator for the orbit evolution with an iterative process for the calculation of impulsive manoeuvres that gives numerical solutions convergent to the optimal values, both for the impulses to be applied and for the times of their implementations, to minimize fuel consumption. Numerical simulations are presented to illustrate this technique and to compare it with classical stationkeeping. The numerical results for this nonlinear approach show how the magnitude of the impulses can be reduced over 3 percent per year with respect to the classical approach. This means that the orbital life-time can be increased up to 5 months for a 15 years life-time mission.