AAS 95-400
Low DV Earth-to-Moon Trajectories
H. J. Pernicka and D. P. Scarberry, Aerospace Engineering Department, San Jose State University, San Jose, CA
Abstract
Most spacecraft on Earth-to-Moon trajectories are limited in their mass by the propulsive requirements to propel such vehicles to the Moon. Of course, any reductions in the propulsive requirements are beneficial since more mass can be delivered to the final destination. The current study has focused on continuing previous research with two primary goals. First, trajectories have been sought that requires V amounts that are "close" to the theoretical minimum given in a prior study, while reducing the time-of-flight. Although a trajectory has not yet been found that uses the minimum V, some relatively low V cases have been obtained. Second, the current study considers the effects from lunar eccentricity and solar gravity. Searching for these trajectories has been attempted primarily through numerical means, i.e., propagation by numerical integration. Discrete Vs are applied at perigee/perilune locations to control the orbit periods so that the perturbing gravitational force from the "third" body (Moon or Earth, and Sun) can be used advantageously.