Optimum Orbital Transfer Using N-lmpulses

Abstract

The problem investigated is the transfer of a space vehicle in an elliptic orbit to a coplanar circular orbit using least characteristic velocity. To achieve this transfer, instantaneous impulses are used. The number of such impulses and the magnitude and direction of any impulse are the unknowns for the analysis. The results of the study establish a class for which two impulses are sufficient to minimize characteristic velocity.