Earth-moon trajectories for the lunar polar orbit mission

Details Earth-moon trajectories for the lunar polar orbit mission Earth-moon trajectories for the lunar polar orbit mission

Oct 1990

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1990dres.iafcz....p&link_type=abstract

IAF, International Astronautical Congress, 41st, Dresden, Federal Republic of Germany, Oct. 6-12, 1990. 10 p.

Astronomy and Astrophysics

Astronomy

Earth Orbital Environments, Earth-Moon Trajectories, Lunar Orbits, Polar Orbits, Fortran, Fuel Consumption, Orbital Launching, Orbital Maneuvers

Scientific paper

The trajectories for a spacecraft sent from LEO to the moon with minimum fuel consumption are calculated assuming that the final orbit around the moon will be polar. Basic parameters are presented for several trajectories to send, insert, and keep a spacecraft in lunar orbit. The numerical results show the following: (1) with the error parameters used, there is no need to use an underburn technique for lunar insertion; (2) the use of low thrust maneuver for the earth-moon phase can significantly save fuel expenditure; and (3) a total velocity increment of less than 100 m/sec, divided among four maneuvers, is sufficient for station-keeping during one year.

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