Transfer of a satellite from high elliptical to geostationary orbit with the help of electric propulsion

被引：0
|
作者：
Salmin, V. V. [1 ]
Petrukhina, K. V. [1 ]
Kvetkin, A. A. [1 ]
机构：
[1] Samara Univ, 34 Moskovskoe Shosse, Samara 443086, Russia
来源：
ELECTRIC PROPULSIONS AND THEIR APPLICATION | 2017年 / 185卷
关键词：
high elliptical orbit; electric propulsion; combined insertion schemes; transport module; local optimal control; electric propulsion thrust; geostationary orbit;
D O I：
10.1016/j.proeng.2017.03.315
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
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. (C) 2017 The Authors. Published by Elsevier Ltd.
引用
收藏
页码：352 / 358
页数：7
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