Well, the different mission profiles is one issue there, another is that we have much more different configurations of a spacecraft here. Also, for the ISS, the Shuttle profile assumes a specific ISS configuration for each mission and the joint-operations are not easy as well. A rendezvous like for Hubble is much easier.
Yes, but how much of an effect does this have on the location and timing of the TI maneuver? The terminal rendezvous phase could differ between the normal ISS missions to Hubble, MIR or even early ISS, but for the most part the ground targeted phase is the same. A bunch of NC maneuvers, sometimes NH or NPC maneuvers and between the last NC maneuver and the TI maneuver some missions had 2 instead of 1 revolution. What I plan to do will set up the TI maneuver at the right place at the right time. Even for Hubble missions that seems to have been 36 minutes before sunset.
Here is the profile I would work on at first. Anything earlier missions did or some specific missions with more complicated procedures like STS-39 could follow later.
The user inputs and calculations for this profile would be:
-Revolutions between OMS2 and NC1. Sometimes that would be 1.5, in this picture 2 revolutions. This could probably change in the iteration if the phase angle is already small, then NC1 should happen at the apogee (relative to the target).
-NC2 happens X revolutions after NC1, is a small correction to NC1 and maybe sets up the NPC maneuver at a node. Not sure, looks like NPC doesn't happen at X or X.5 revolutions after NC2.
-NPC happens at a node, maybe a few revolutions after NC2, if necessary. Seems to be about half way between NC2 and NC3.
-NC3 is the second major phasing maneuver. The combination of NC1 and NC3 sets up the timing for TI. A user input would be the revolutions between NC1 and NC3, 9.5 in this case. But this can change in the iteration if the TI timing doesn't work out with that number.
-NH is a small correction like NC2 so that NC4 happens at the correct relative DH on the R-Bar.
-NC4 sets up the TI maneuver at the correct relative position to the target. Usually 1 sometimes 2 revolutions between NC4 and TI.
-NCC is onboard targeted. But there is also a ground solution which has to be calculated. No problem to calculate that, even the Lambert MFD I published on Orbithangar can do that.
-The other maneuvers are all targeted onboard and a ground solution would be calculated as appropiate.
I realize this is the standard profile which was often deviated from, but this should basically be valid for Hubble, MIR and ISS.
