Selection of design parameters of a spacecraft electric propulsion engine ensuring the geostationary orbit raising mission
- Authors: Kolesov A.V.1, Salmin V.V.1
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Affiliations:
- Samara National Research University
- Issue: Vol 23, No 3 (2024)
- Pages: 31-41
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/27906
- DOI: https://doi.org/10.18287/2541-7533-2024-23-3-31-41
- ID: 27906
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Full Text
Abstract
The problem of selecting suboptimal parameters of an electric propulsion system as part of a spacecraft, ensuring a geostationary orbit raising mission using a Soyuz-5 launch vehicle at the initial launch stage, is investigated. An expression is obtained for the main optimality criterion – the payload relative mass. An algorithm is obtained for solving the problem of parametric optimization of an electric propulsion system as part of a hybrid transportation system. The task of selecting the optimal electric propulsion engine for launching a spacecraft with an electric propulsion system to a geostationary orbit using the launch vehicle under consideration is solved. A design ballistic calculation and a comparative analysis of the obtained data are performed.
About the authors
A. V. Kolesov
Samara National Research University
Author for correspondence.
Email: kolesov19930720@mail.ru
Engineer
Russian FederationV. V. Salmin
Samara National Research University
Email: sputnik@ssau.ru
Doctor of Science (Engineering), Professor, Chief Researcher at the Institute of Space Engineering
Russian FederationReferences
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