  In this paper, a practical approach to the trajectory design for asteroid
exploration missions with CubeSats is presented. When applied trajectories are
sought, operative concerns and uncertainties affecting the spacecraft dynamics
must be considered during the design process. Otherwise, trajectories that are
possible on paper might become unfeasible when real-world constraints are
considered. The risk of such eventualities leads to the urge of extending the
trajectory design focus on the uncertainties affecting the dynamics and on the
operative constraints derived by ground operations. This is especially true
when targeting highly perturbed environments such as small bodies with low-cost
solutions as CubeSats, whose capabilities in deep-space are still unknown. The
case study presented is the Milani CubeSat which will be launched in 2024 with
Hera in the frame of the AIDA mission.
