Multistep algorithms for the orbit control of geostationary spacecraft using low thrust engine

Abstract

The problem of terminal control of orbit of geostationary spacecraft is formulated. The control is realized by means of a small transversal acceleration generated by a low-thrust electric propulsion engine. Only the plane parameters of the orbit that determine the position of the geostationary spacecraft in the orbit plane, namely, the orbital period, the eccentricity and the longitude of the standing point, are considered. The problem of terminal control is solved using multistep algorithms. The paper provides an overview of the developed multistep algorithms to control plane parameters of the orbit of geostationary spacecraft. In General, the control law is given by the sequence of durations of low-thrust engines. Deals with numerical multistep control algorithm, when the control law specifies a decreasing sequence of durations of the work of engines. Discusses the three-step control algorithm to control plane parameters of the orbit, which is based on the analytical solution of problem of terminal control of the geostationary spacecraft orbit. The results of simulation of the geostationary spacecraft orbit control using the developed multistep algorithms.