The problem of transfer orbits from one body back to the same body

The problem of transfer orbits from one body back to the same body (the Moon or a planet) is formulated as a Lambert's problem and solved by Gooding's Lambert routines. We consider elliptic as well a circular orbits for the Moon or a planet and any kind of orbit (elliptic, parabolic, or hyperbolic) for the spacecraft. The solutions are plotted in terms of the true anomaly instead of the eccentric anomaly) for several cases. We show that the use of the true anomaly simplifies the solutions in several ways. We also solved the problem of transfers from this body to the corresponding L4 and L5 points. After that, the same problem is studied in terms of the V and the time required for the transfer. Among all the possible transfer orbits, a small family with almost zero V was found. The properties of these orbits are shown in details.