Search for Low Delta V Earth-To-Moon Trajectories
A search for low Δ V Earth-to-Moon trajectories has been initiated. Numerical integration of the equations of motion from the circular restricted three-body problem has resulted in the computation of a trajectory that saves more than 100 m/s over a Hohmann transfer, although the flight time is almost ten months. The approach used involves the computation of two trajectory 'legs': first, a trajectory from low Earth orbit to the L1 libration point of the Earth-Moon system, and second, a trajectory from L1 to an orbit about the Moon. Multiple orbits about Earth using lunar perturbations facilitates the transfer to L1. Similarly, the L1 to Moon leg uses the perturbation from the Earth to achieve a low orbit about the Moon. Small maneuvers are used in both legs to control the orbital period so the third body perturbations can be used advantageously.
H. J. Pernicka et al., "Search for Low Delta V Earth-To-Moon Trajectories," Journal of the Astronautical Sciences, American Astronautical Society, Jan 1995.
Mechanical and Aerospace Engineering
Keywords and Phrases
Computational Methods; Equations of Motion; Integration; Lunar Missions; Maipulators; Spacecraft
International Standard Serial Number (ISSN)
Article - Journal
© 1995 American Astronautical Society, All rights reserved.
01 Jan 1995