First post on these forums, hope it is in the right place. I do apologize if it isn't.

I've been looking at optimum circular parking orbits that would give the lowest delta-V boost for a Hohmann transfer to Mars using the patched conics approximation.

I've been following the methods in the paper

"EFFICIENT PLANETARY PARKING ORBITS WITH EXAMPLES FOR MARS"

By Roger W. Luidens and Brent A. Miller

Lewis Research Center

From my calculations, the Earth-departure parking orbit that would give the lowest delta-V boost for the mission is at approximately r= 91940 km, which is pretty high compared to the norm.

Not being familiar with the launch phase of missions, I wanted to know how would a spacecraft get up to that kind of altitude? Would it have a direct ascent to some altitude in LEO before burning again to reach that circular orbit, and hence incurring an extra delta-V, making going to the optimum parking orbit pointless?

Or would it directly ascend to that altitude? If it directly ascended to that altitude, again, would the delta-V losses due to drag be so great that it would negate the savings of the optimum circular parking orbit? Is there any way for me to estimate what these losses might be?'

If the efficient circular parking orbit is not the way to go, how should I select the parking orbit for the mission?