A real time spacecraft guidance formulation based upon optimization theory

This 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.