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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...
This paper considers a combined scheme of insertion of a satellite into a geostationary orbit with the help of high and low torque thrusters. The start orbit is high elliptical and is formed by the third stage of the launch vehicle. Further insertion is performed by an electric propulsion unit. The trajectory of insertion, transfer time and propellant mass have been calculated.
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