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Tonight, I decided to fly a rendezvous mission to Earth's Moon, I flew an XR2 from Earth Orbit to the Moon in a 24 hour trajectory, then rendezvoused with an orbiting XR2 I had already placed in lunar orbit. The flight was one of my best, I pulled off a good synchronization of the orbits around the moon, and docked relatively well. My synching needs some work, but I know what to do about that. But my issue came when I was targeting the XR2 in lunar orbit. In IMFD, I didn't see how I could fine tune my arrival to coincide with the target vessel being at a certain point of its orbit. I had thought that IMFD's Planet Approach program would display the white line showing where the target would be, at the closest approach of my planned orbit, but it did not. I tried looking in the map program, but didn't find anything either. I ended up dropping into a higher orbit, but because I arrived behind the target, had to drop into a lower orbit and catch up to it which took more time and fuel than I intended. Am I missing something here? If IMFD doesn't have this built-in, is there a good method for estimating or eyeballing this?
One idea I had but didn't want to test out right then is to use the orbital period of the target, and my time to periapsis, and work out something that way (sorry, it's late and I didn't work out the exact methodology), and while that would have worked perfectly today since my target was in an almost perfectly circular orbit with its periapsis coinciding with mine, I don't think that would work on an elliptical orbit since the angular velocity varies from point to point. Perhaps it could be done, but that starts getting very math-heavy.
Thanks for any help or suggestions!
Matt
One idea I had but didn't want to test out right then is to use the orbital period of the target, and my time to periapsis, and work out something that way (sorry, it's late and I didn't work out the exact methodology), and while that would have worked perfectly today since my target was in an almost perfectly circular orbit with its periapsis coinciding with mine, I don't think that would work on an elliptical orbit since the angular velocity varies from point to point. Perhaps it could be done, but that starts getting very math-heavy.
Thanks for any help or suggestions!
Matt
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