Article ID Journal Published Year Pages File Type
5028771 Procedia Engineering 2017 7 Pages PDF
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.

Related Topics
Physical Sciences and Engineering Engineering Engineering (General)
Authors
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