A guidance scheme for vehicle flight from lunar orbit to a prescribed point on a spherical, non-rotating moon is presented. The equations of motion have been simplified only to perm it a closed solution for the thrust magnitude and thrust direction. The trajectory computations them selves are made under more realistic and accurate assumptions and are not included.
Summary: "Based on Lawden's equation, semi-explicit,'iterative' Saturn guidance equations are derived, many were successfully flight tested on Saturn I and analyzed for the main Apollo mission and other applications applications."
