This paper addresses the computation of the required trajectory
correction maneuvers for a halo orbit space mission to compensate
for the launch velocity errors introduced by inaccuracies of the
launch vehicle. By combining dynamical systems theory with optimal
control techniques, we are able to provide a compelling portrait of
the complex landscape of the trajectory design space. This approach
enables automation of the analysis to perform parametric studies
that simply were not available to mission designers a few years ago,
such as how the magnitude of the errors and the timing of the 6rst
trajectory correction maneuver affects the correction
V. The
impetus for combining dynamical 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.