Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
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Final ascent to the geostationary orbit with the electric propulsion engine

Published: 26.02.2016

Authors: Yakovlev A.V., Vnukov A.A., Balandina T.N.

Published in issue: #2(50)/2016

DOI: 10.18698/2308-6033-2016-2-1466

Category: Aviation and Rocket-Space Engineering | Chapter: Aircraft Dynamics, Ballistics, Motion Control

The article describes the analysis of the schemes of completing spacecraft launch into geostationary orbit (GSO ) using the electric propulsion system, the assessment of propellant mass and time consumption, and the required values of these parameters for completing spacecraft launch into the geostationary orbit from a transfer orbit. The family of transfer orbits was compared to determine the effectiveness of completing spacecraft launch. The problems associated with spacecraft stay in Earth's radiation belt are discussed. The advantages of completing launch of the spacecraft equipped with electric propulsion systems into the GSO are demonstrated.

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