Optimization of project-ballistic parameters for low earth orbit spacecraft with propulsion systems with energy storage
- Авторы: Khramov A.1, Ishkov S.1
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Учреждения:
- Samara University
- Выпуск: Том 59, № 3 (2016)
- Страницы: 351-357
- Раздел: Flight Dynamics and Control of Flight Vehicles
- URL: https://journals.rcsi.science/1068-7998/article/view/229760
- DOI: https://doi.org/10.3103/S1068799816030090
- ID: 229760
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Аннотация
Optimization of project-ballistic parameters of the spacecraft with propulsion systems with energy accumulation during the orbital transfer between low Earth orbits in the non-central gravitational field of the Earth is considered. The mass model of the spacecraft with an uncontrollable power-limited engine with the energy accumulator is used. The method of the project-ballistic optimization is obtained as an iterative procedure. Energy storage usage efficiency during the orbital transfer between low Earth orbits is estimated.
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Об авторах
A. Khramov
Samara University
Автор, ответственный за переписку.
Email: hramovaa76@rambler.ru
Россия, sh. Moskovskoye 34, Samara, 443086
S. Ishkov
Samara University
Email: hramovaa76@rambler.ru
Россия, sh. Moskovskoye 34, Samara, 443086