The characteristics of three precision circumlunar trajectories are presented for use in the study of a manned mission in the year 1968. These trajectories have been obtained with the use of a restricted four-body, three-dimensional trajectory program utilizing actual calendar dates and body positions as obtained from U.S. Naval Observatory data. The constraints associated with each of these trajectories are launch from Cape Canaveral, Florida, touchdown in the continental United States, and injection conditions compatible with the capabilities of a booster such as the Saturn vehicle. The injection dates were selected to obtain the trajectory characteristics associated with each of the lunar motions which may be encountered, with a direct launch from Cape Canaveral, that is whether the moon is descending, ascending, or at maximum nega¬tive declination at the time of periselenian passage.
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