There is a spacecraft on an *initial* orbit. There is a *target* orbit.
The Keplerian elements are given for the orbits.

The problem is: when and what $\Delta V$ to apply to the SC to move it to the target orbit in the *optimal* way (with minimum fuel consumption). Impulsive maneuvers are considered.


The problem would be easier, if we know the target point (i.e rendezvous problem), in this case I could solve the Lambert problem. What to do in my case (when any point of target orbit may be chosen)?

The question is related to arbitrary orbits. However, if it's required to make the question more specific, we can consider the following orbits: the initial orbit is sun-synchronous, the target orbit is elliptic, with inclination of 63, apogee at 8000km and perigee at 600km.