Abstract:
The trajectory of expedition to Mars and its satellite Phobos with returning to the Earth is optimized. The attraction of the Sun or the Earth or Mars is considered at each part of the trajectory. The Earth and Mars positions correspond to ephemerides DE424, and the position of Phobos — to ephemerides MAR097. Not more than 6 impulses are assumed at the trajectory. Spacecraft must start from the Earth in the period of 2020–2030 and stay at Phobos at least for 30 days. The total time of the expedition is limited to 1500 days. The characteristic velocity is minimized.
Key words:interplanetary transfer optimization, expedition to Phobos, Lambert's problem.
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