This is a continuation of work presented at the Second GRO Science Workshop.1It includes computations with much reduced timing errors as well as those for the PVO/Ulysses/GRO/GRANAT configuration. These could be done so quickly because the general coplanar problem of Taff’s2method is explicitly solvable. Given this, and the nearness of any actual spacecraft configuration to alignment with the ecliptic, both an initial guess and a rapidly converging numerical algorithm for the general situation can be formulated. Finally, since the timing errors dominate the observational errors, one can analytically compute the error distributions. Thus, Taff’s method is shown to be numerically robust, accurate, and analytically convenient.