Placement of the next space outpost, after the low-earth-orbit space station, will strongly affect the evolution of future space programs. The outpost will store rocket fuel and offer a haven to space workers, as well as provide a transportation depot for long missions. Ideally, it must be loosely bound to the earth, easy to approach and leave, and available for launch at any time. One Lagrange equilibrium point, L sub 1 (SE), between the sun and the earth and another, L sub 2 (EM), in the earth-moon system have excellent physical characteristics for an outpost; L sub 1 (SE), for example, requires less than 2% additional rocket propellant for docking there on the way to Moon bases or Mars bases. We apply the rocket problem, the two-body problem, and the three-body problem in discussing alternative locations for space depots. We conclude that Lagrange point halo orbits are the standard by which other concepts for transportation depots must be gauged. 12 refs., 6 figs. (ERA citation 11:006480)
Moon Base/Mars Base Transportation Depot
1985
15 pages
Report
Keine Angabe
Englisch
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