A Moon Base/Mars Base Transportation Depot
Abstract
Two Lagrange equilibrium points, L1(SE) between the sun and the earth, and L2(EM) in the earthmoon system, are presently noted to have excellent characteristics for a space outpost beyond the low earth orbit Space Station. The rocket problem, the twobody problem, and the threebody problem are presently applied to a consideration of alternative locations for space depots. It is concluded that Lagrange point halo orbits are the standard by which alternative concepts for transportation depots must be gauged.
 Publication:

Lunar Bases and Space Activities of the 21st Century
 Pub Date:
 1985
 Bibcode:
 1985lbsa.conf..141K
 Keywords:

 Celestial Mechanics;
 Lunar Bases;
 Mars Surface;
 Space Bases;
 Space Transportation;
 EarthMoon System;
 Lagrangian Equilibrium Points;
 Space Commercialization;
 Three Body Problem;
 Two Body Problem;
 Astrodynamics