Q Max,
You bring an interesting increase in depth to the discussion, and are some what correct, in that the type of rotor head does affect the angle, and the disk angle can be different than the fuselage angle, but the idea that the thrust must pass through the CG is actually quite a bit off, unless you are flying a teetering rotor helicopter. The old idea that thrust is the only product of the rotor is brought about by the fact that all the old training manuals assume a teetering rotor, and were written for a simpler time!
A few threads ago I discussed the moment produced by an articulated rotor, and illustrated the concept of how any cyclic flapping produces a powerful moment that is transmitted through the mast to help control the aircraftr. The moment produced is quite large, and for articulated and rigid systems, produces a clear mismatch between the line of action of the rotor thrust and the cg.
In a nutshell, most helos tend to have a fuselage tilt that approximates the disk tilt (usually a bit less fuselage tilt, due to the head moment due to flapping). Rigid rotors have the most, and teetering rotors have the least.
Thanks, Q Max for opening the discussion!!