How are orbit insertion changes in altitude and RAAN designed?

Question

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?

Answer 1

Altitude is usually via a burn at the apogee/ perigee, as you mentioned.

RAAN changes are usually done over time. If you are slightly over or under your target orbit, your RAAN will drift over time. This may take weeks to months, but you will eventually get there, without the expenditure of a lot of fuel.

Of some note is that there are some orbits that don't appear to have an RAAN drift, like sun-synchronous orbits. Those orbits actually require a specific altitude to achieve that no drift state, and thus if they are higher/ lower, they will actually still drift with time.