Trajectory options for a manned mission to mars using high-thrust propulsion systems

Автор: Arkhangelskiy Nikolay Ivanovich, Muzychenko Evgeny Igorevich, Sinitsin Aleksey Andreevich

Журнал: Космическая техника и технологии @ktt-energia

Рубрика: Динамика, баллистика, управление движением летательных аппаратов

Статья в выпуске: 3 (34), 2021 года.

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An analysis has been done of performance factors (mission duration, initial mass of the interplanetary crew transfer vehicle, velocity of the re-entry into the Earth atmosphere of the descent vehicle with the crew) for a single-spacecraft manned mission to Mars using high-thrust propulsion systems. Locally optimal solutions (in terms of delta-V budgets for the transfer) were found for the Earth-Mars-Earth transfer, with varying periods of waiting in Mars orbit, minimal distance to the Sun, as well as flight paths (direct Earth-Mars-Earth transfers vs. gravity assist maneuvers at Venus during Earth-Mars or Mars-Earth transfers). The proposed classification for locally optimal solutions is applicable to both high-thrust propulsion systems and low-thrust propulsion systems. A comparison of performance factors has been done for manned Martian mission options based on liquid-propellant engines and nuclear rocket engines with a 12,5 km/s constraint on the velocity of the manned re-entry vehicle in the Earth atmosphere.


Manned mission to mars, interplanetary transfer trajectory, high-thrust, liquid-propellant rocket engine, nuclear rocket engine, mission duration, initial mass of the interplanetary vehicle, re-entry velocity of a manned vehicle for returning the crew to earth


Короткий адрес:

IDR: 143177957   |   DOI: 10.33950/spacetech-2308-7625-2021-3-96-110

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