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Low-thrust enabled highly non-Keplerian orbits in support of future Mars exploration

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Figure

Fig. 1 The rotating coordinate frame and the spacecraft position therein for the restricted three-body problem
Fig. 2 Artificial equilibrium points for the Sun-Mercury L1projected onto the planes perpendicular to and parallel to the orbital plane (left), and the equithrust surface /L2 system depicted by equithrust contours equivalent to an acceleration of 0.3mms-2
Fig. 3 Non-Keplerian orbit equithrust contours projected onto the plane perpendicular to the orbital plane for the Sun-Mars-spacecraft 3-body system for SEP spacecraft (left) and solar sail (right) of equivalent acceleration
Table 1: Potential of non-Keplerian orbits (NKOs) throughout the Solar System
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