A SEARCH FOR LOW DELTA-V EARTH-TO-MOON TRAJECTORIES

A search for low Delta V Earth-to-Moon trajectories has been initiated . Numerical integration of the equations of motion from the circular r estricted three-body problem has resulted in the computation of a traj ectory that saves more than 100 m/s over a Hohmann transfer, although the flight time is almost ten months. The approach used involves the c omputation of two trajectory ''legs'': first, a trajectory from low Ea rth orbit to the L(1) libration point of the Earth-Moon system, and se cond, a trajectory from L(1) to an orbit about the Moon. Multiple orbi ts about Earth using lunar perturbations facilitates the transfer to L (1). Similarly, the L(1) to Moon leg uses the perturbation from the Ea rth to achieve a low orbit about the Moon. Small maneuvers are used in both legs to control the orbital period so the third body perturbatio ns can be used advantageously.