This paper addresses the computation of the required trajectory correction
maneuvers (TCM) for a halo orbit space mission to compensate for the launch velocity
errors introduced by inaccuracies of the launch vehicle. By combiningdynamical
systems theory with optimal control techniques, we produce a portrait of the complex
landscape of the trajectory design space. This approach enables parametric studies
not available to mission designers a few years ago, such as how the magnitude of the
errors and the timingof the first TCM affect the correction ΔV. The impetus for
combiningdynamical systems theory and optimal control in this problem arises from
design issues for the Genesis Discovery mission being developed for NASA by the Jet
Propulsion Laboratory
