Conceptual design of the solar electric propulsion system for the manned mission to Mars based on the technology of the immediate future
- Paper number
IAC-06-A5.P.09
- Author
Dr. Vladimir Obukhov, RIAME MAI, Russia
- Coauthor
Prof. Garri Popov, RIAME MAI, Russia
- Coauthor
Dr. Vladimir Kim, RIAME MAI, Russia
- Coauthor
Dr. Vladimir Kulkov, RIAME MAI, Russia
- Coauthor
Prof. Garri Popov, RIAME MAI, Russia
- Coauthor
Mr. V.M. Murashko, Russia
- Coauthor
Mr. S.V. Ivanov, Lavochkin Association, Russia
- Year
2006
- Abstract
Basic idea for the conceptual design of the solar electric propulsion system (SEPS) intended for the manned Martian mission is in the endeavor to show that in view of the near-term perspectives such complicated mission may be considered as quite feasible at the present level of space engineering. Mission plan comprises the following stages, at which sustainer SEPS should be used: 1 – transfer of the Martian expedition complex (MEC) from assembly orbit (AO) to high earth orbit (HEO), to which the crew is delivered, 2 – formation of the departure trajectory, 3 – interplanetary heliocentric trip from HEO to the intermediate orbit of Mars satellite (IOMS) that is close to circular, 4 – MEC transfer from IOMS to the low circular base line orbit of Mars satellite (BLOMS) (at that BLOMS is the orbit of debarkation and embarkation of a part of Martian research crew), 5 – MEC return interplanetary flight from IOMS to HEO. Two variants of MEC configuration were considered, respectively: of a modern MEC based on the actual level of electric propulsions and photoconverters and of a prospective MEC that takes into account predicted technological progress in these fields in the near-term future. For the modern MEC concept an EPS option is studied that has specific impulse of 30000 m/s and maximum power consumption of 5 MW securing the crew return on board RU of 60 ton in mass to the return orbit. Mass balance of EPS units for this option is very strained, and this is the reason for substantial development risk in securing tight development schedule. EPS option with specific pulse of 35000 m/s and maximum power consumption of 5.5 MW secures delivery of RU of 90 ton in mass at the initial MEC mass of 560 ton. The development of the prospective MEC may be based on the existing prototypes and carried out up to the stage of flight models during 10…15 years beginning from the full-size financing start.
- Abstract document