Assuming that desired inclination is achieved during the launch, how are the target altitude and RAAN usually achieved in satellite missions, if the launch could only place the satellite on a different orbit?
I understand that any change plane is cheaper at apoapsis, and that a change in RAAN without changing the inclination is only achievable at 90 degrees anomaly from the line of apses. I also believe that oftentimes the satellites are taken to much higher orbits (via Hohmann? Lambert?) where the plane change is cheaper, and then taken down to the desired orbit in a combined maneuver sequence.
Even if circular orbits were assumed, there seem to be a lot of different possible combinations.
How is this problem usually approached in preliminary mission design?