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One small update. I haven't had much time working on the MFD, but I am making some progress working on the Launch Window/Launch Targeting Processor. It consists of those two parts, a launch window calculation which calculates the liftoff time based on in-plane or phase angle and then a launch targeting part which calculates a more precise, zero yaw steering preferred liftoff time and also launch targeting parameters (inclination and descending node angle).
I have various, incomplete sources on this processor, which make the work interesting and challenging. There definitely is a direct heritage from Gemini (launching to intercept another Gemini spacecraft or an Agena) to the planned, but never flown AS-207/208 mission (two Saturn IBs launching a CSM and LM respectively, flying an Apollo 9 kind of mission) to Skylab and then to Shuttle. Other than the OMP the LWP/LTP will probably not end up working just like the real thing, as it was at the end of the Shuttle program. There are some numbers you would have to generate externally (the descending node angle for a specific inclination and time into launch window) and I don't fully understand how that would be used anyway. After all the documentation I have, other than the FDO Console Handbook, are all from 1980 or earlier. But it will still be very close to what the FDOs used on launch day to generate the exact launch window and targeting parameters.
While SSU doesn't do any second stage yaw steering yet it should probably be possible to intercept a specific orbit by using the right inclination and a biased launch time. The launch time is calculated with an analytical bias anyway, the Console Handbook uses the input value of 5m40s before the in-plane time. And for a set of specific inclination, launch weight and insertion parameters the necessary time bias should be fairly constant, it will just need a bunch of trial and error. My initial tests suggest that the 5m40s value needs to be changed by about 20 seconds. One LTP output is a post-MPS dump state vector, which can be used in the OMP to check if the orbital plane is right and any NPC maneuver in the rendezvous plan is near zero. That is especially relevant for the non-spherical gravity.
Parallel to this I'll implement this processor for NASSP as well and will try to fly a Skylab rendezvous profile with it. The simulated LVDC can do insertion into a specific orbital plane very well.
I have various, incomplete sources on this processor, which make the work interesting and challenging. There definitely is a direct heritage from Gemini (launching to intercept another Gemini spacecraft or an Agena) to the planned, but never flown AS-207/208 mission (two Saturn IBs launching a CSM and LM respectively, flying an Apollo 9 kind of mission) to Skylab and then to Shuttle. Other than the OMP the LWP/LTP will probably not end up working just like the real thing, as it was at the end of the Shuttle program. There are some numbers you would have to generate externally (the descending node angle for a specific inclination and time into launch window) and I don't fully understand how that would be used anyway. After all the documentation I have, other than the FDO Console Handbook, are all from 1980 or earlier. But it will still be very close to what the FDOs used on launch day to generate the exact launch window and targeting parameters.
While SSU doesn't do any second stage yaw steering yet it should probably be possible to intercept a specific orbit by using the right inclination and a biased launch time. The launch time is calculated with an analytical bias anyway, the Console Handbook uses the input value of 5m40s before the in-plane time. And for a set of specific inclination, launch weight and insertion parameters the necessary time bias should be fairly constant, it will just need a bunch of trial and error. My initial tests suggest that the 5m40s value needs to be changed by about 20 seconds. One LTP output is a post-MPS dump state vector, which can be used in the OMP to check if the orbital plane is right and any NPC maneuver in the rendezvous plan is near zero. That is especially relevant for the non-spherical gravity.
Parallel to this I'll implement this processor for NASSP as well and will try to fly a Skylab rendezvous profile with it. The simulated LVDC can do insertion into a specific orbital plane very well.