Dawkins, George S.2022-10-282022-10-28197213848793https://hdl.handle.net/10657/12454This thesis is concerned with the development of a spacecraft guidance which will solve the problem associated with the optimum transfer of a spacecraft between two states. The theoretical development of an existing guidance formulation is shown and this formulation is extended to include a more general mission capability. Specifically, the guidance formulation presented is extended to an operational capability for low-thrust maneuvers. Numerical results are presented which compare the guidance solution and a near optimal solution to the same low-thrust transfer problem. These results indicate that the guidance procedure can be extended to an operational capability for low-thrust maneuvers with performance (propellant expenditure) comparable to an optimum transfer.application/pdfenThis item is protected by copyright but is made available here under a claim of fair use (17 U.S.C. Section 107) for non-profit research and educational purposes. Users of this work assume the responsibility for determining copyright status prior to reusing, publishing, or reproducing this item for purposes other than what is allowed by fair use or other copyright exemptions. Any reuse of this item in excess of fair use or other copyright exemptions requires express permission of the copyright holder.Thesisreformatted digital