For example, for a Mars-bound spacecraft, when are the available launch windows for the next ten years? How do the launch C3 requirements vary for each launch window? While it may be possible to determine trajectory requirements to a single well-known body such as Mars from published tables [1], it is usually not possible to do so for missions to small-bodies, a class of celestial bodies that are of increasing interest to space agencies for both robotic and human exploration. For example, if performing a design study for an asteroid sample-return mission, one would want to know what objects larger than 1 km can be reached during a given launch year and with given mission duration and ΔV (indicator of propellant requirements) constraints.