Many years ago there was a claim that the Eagle was lost on the surface and it was incredulous to suggest that the ascent stage could find a correct orbit to rendezvous with the CM. (Might be fattydash). The demands of this problem are mind boggling, but even more mind boggling is something I found during the LM stability debate. This snippet from Clavius
Most importantly, the lunar module had not one, but two separate computer-based guidance systems. One was built around the same hardware as the command module's guidance computer. The other was much simpler and could only be used to abort the landing and/or return to orbit.
How did the abort guidance work such that the LM could make an accurate rendezvous with the CM? Was there some kind of approximate LM parking orbit before finer adjustments to LM/CM orbits were made?
I also understand the abort system was also used during Apollo 11 descent. How was it used in this context? Was it an override allowing manual control.
Hope the questions make sense.
