Довыведение космических аппаратов на геостационарную орбиту с помощью электрореактивных двигателей

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А.В. Яковлев, А.А. Внуков, Т.Н. Баландина
10 Инженерный журнал: наука и инновации # 22016
Final ascent to the geostationary orbit
with the electric propulsion engine
© A.V. Yakovlev, A.A. Vnukov, T.N. Balandina
JSC Academician M.F. Reshetnev “Information Satellite Systems”, Zheleznogorsk,
662971, Krasnoyarsk Region, Russia
The article describes the analysis of the schemes of completing spacecraft launch into
geostationary orbit (GSO ) using the electric propulsion system, the assessment of pro-
pellant mass and time consumption, and the required values of these parameters for
completing spacecraft launch into the geostationary orbit from a transfer orbit. The fami-
ly 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 dis-
cussed. The advantages of completing launch of the spacecraft equipped with electric
propulsion systems into the GSO are demonstrated.
Keywords: spacecraft, geostationary orbit, transfer orbit, electric propulsion system,
effectiveness of completing spacecraft launch.
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