GLSNightPilot
You may well be correct, since I am only working with theory. Stability and control can be at opposite ends of the spectrum, but I am hoping that a 'rotor hub offset' will reduce the delay in the rotor's response to cyclic inputs, without being detrimental to stability. Does this sound feasible?
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helmet fire
There is no disagreement with your Statement
" Individual blades CAN AND DO flap on two bladed rotor systems ". I was, perhaps over simplistically, trying to cover the basic activity of the teetering rotor. The amount of undersling on a teetering rotor is set for the mean operational condition. Flight activity such as changes in thrust will increase and decrease the coning angle. Maneuvers will cause blade flexing. Both will pull the rotor's actual center(s) away from the fixed teetering center, and vibration will occur.
Oh!! for an Absolutely Rigid Rotor
I agree that there is lead-lag in the blades but the blades on a teetering rotor will primarily lead-lag in unison. This puts a loading on the mast but not between the two blades. Correct me if I'm wrong, but I think that the Hookes joint effect (or call it cyclic Coriolis effect) is the primary reason for the lead-lag. Out of plane flexing of the blades splits the centers and causes vibration.