In previous work, it was shown that determination of orbit during and after moon passage to lowest order requires determination of correction term to Keplerian solution for approach orbit, expressed in terms of certain integrals; summary of theoretical results; relevant integrals are evaluated numerically so that motion during and after moon passage can be related to initial conditions near earth; Keplerian integrals for motion during moon passage obtained by present first-order theory are compared with exact values calculated on IBM computer 7094 for 27 orbits.
Numerical aspects of uniformly valid asymptotic approximations for class of trajectories in restricted three-body problem
Progress Astronautics Aeronautics -- Celestial Mechanics Astrodynamics
1964
31 pages
Article (Journal)
English
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