Research Article
Optimal Two-Impulse Trajectories with Moderate Flight Time for Earth-Moon Missions
Figure 14
Multiple revolution ascent, clockwise LMO arrival, km/s, km/s, days, deg.
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(a) Earth-Moon trajectory, inertial coordinate frame |
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(b) LEO departure, inertial coordinate frame |
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(c) LMO arrival, inertial coordinate frame |
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(d) Earth-Moon trajectory, rotating coordinate frame |
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(e) LEO departure, rotating coordinate frame |
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(f) LMO arrival, rotating coordinate frame |
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