Application of Electric Propulsion for Low Earth Orbit Station Keeping

This paper considers the problem of keeping a low Earth elliptical orbit of a satellite by low thrust electric propulsion. The main disturbance is the aerodynamic drag. Its precise value is not known well enough. Suggested correction algorithms imply: 1) stepwise verification of the perturbation force by direct measurement; and 2) calculation of control parameters by approximate analytical relations. Results of modeling the processes of satellite motion control are given.