  For deep-space mission design, the gravity of the Sun and the Moon can be
first considered and utilized. Their gravity can provide the energy change for
launching spacecraft and retrieving spacecraft as well as asteroids. Regarding
an asteroid retrieval mission, it can lead to the mitigation of asteroid
hazards and an easy exploration and exploitation of the asteroid. This paper
discusses the application of the Sun-driven lunar swingby sequence for asteroid
missions. Characterizing the capacity of this technique is not only interesting
in terms of dynamic insights but also non-trivial for trajectory design. The
capacity of a Sun-driven lunar swingby sequence is elucidated in this paper
with the help of the "Swingby-Jacobi" graph. The capacity can be represented by
a range of the Jacobi integral that encloses around 660 asteroids currently
cataloged. To facilitate trajectory design, a database of Sun-perturbed
Moon-to-Moon transfers, including multi-revolution cases is generated and
employed. Massive trajectory options for spacecraft launch and asteroid capture
can then be explored and optimized. Finally, a number of asteroid flyby,
rendezvous, sample-return, and retrieval mission options enabled by the
proposed technique are obtained.
