Article ID | Journal | Published Year | Pages | File Type |
---|---|---|---|---|
5028771 | Procedia Engineering | 2017 | 7 Pages |
Abstract
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.
Keywords
Related Topics
Physical Sciences and Engineering
Engineering
Engineering (General)
Authors
V.V. Volotsuev, V.V. Salmin, S.L. Safronov, V.V. Stratilatov, I.S. Tkachenko, S.S. Raube, S.V. Shikhanov, E.G. Shikhanova,