Сибирский журнал науки и технологий
ISSN 2587-6066

Vestnik sibsau
Vestnik sibsau
Vestnik sibsau
Vestnik sibsau

UDK 629.78: 629.036 Doi: 10.31772/2587-6066-2018-19-3-489-496
Yu. M. Yermoshkin*, D. V. Volkov, E. N. Yakimov
JSC “Academician M. F. Reshetnev “Information Satellite Systems” 52, Lenina Str., Zheleznogorsk, Krasnoyarsk Region, 662972, Russian Federation *E-mail: erm@iss-reshetnev.ru
Over the past several years the concept of the so-called “all electric propulsion spacecraft” has gained popularity among both customers and developers of geostationary (GEO) spacecraft; this issue is being actively discussed. The main advantages of the concept are the following: decreasing the mass of spacecraft and increasing its economic efficiency by means of pair orbital injection. There are some illustrative cases of implementation of this concept by American, European and Russian companies. However, specialists interpret the content of the concept in different ways. That causes the problems connected to the development of the conceptual design of spacecraft. It is therefore very important to consider the concept in more detail, to compare various points of view in order to form understanding reflecting its essence the most accurately. At the same time, on the basis of the available examples, it would be feasible to analyze the advantages and disadvantages of this concept in comparison with other approaches to the construction of propulsion system of spacecraft. In the article we offer to interpret the concept as “All electric propulsion spacecraft”. This interpretation allows to understand its content unambiguously by the specialists of both Russian and Western Technical Schools. We offer to define “All electric propulsion spacecraft” as an apparatus that does not have in its composition an apogee engine unit that is chemically fuelled. It has to execute manoeuvres on geostationary orbit raising, orbit correction and momentum wheel unloading by electrical propulsion only. We have shown that with the existing level of excellence of the equipment this concept does not have any advantages over the concept of separate propulsion subsystems for the correction and orientation by total mass as well as by the level of reliability.
Keywords: all electric propulsion spacecraft, apogee thruster, propulsion subsystem, electric propulsion engine, orbit raising.

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Yermoshkin Yury Mikhaylovich – Cand. Sc., Docent, head of Propulsion department, JSC “Academician M. F. Reshetnev “Information Satellite Systems”. E-mail: erm@iss-reshetnev.ru.

Volkov Dmitry Viktorovich – head of Propulsion sector, JSC “Academician M. F. Reshetnev “Information Satellite Systems”. E-mail: dmitri@iss-reshetnev.ru.

Yakimov Evgeny Nikolaevich – head of Attitude control and propulsion division, JSC “Academician M. F. Reshetnev “Information Satellite Systems”. E-mail: Yen@iss-reshetnev.ru.