To: delta3
Your remarks are correct, static neutrality occurs when the pitch horn is aligned.
Aligned with what?
So applying first order reasoning this means that the rotor should tip say 20 degrees later.
Later than what?
OK let's consider phase angle and phase angle shift. As I had indicated previously my explanation of phase angle is the adding of the pitch horn lead to the angle at which the swashplate tilts with forward cyclic. And phase angle shift is the number of degrees the blade actually responds to forward cyclic input and this shift is to the right of the longitudinal axis.
The examples I gave were the Sikorsky system (45-degree pitch horn and a 45-degree swashplate tilt in reference to the cyclic movement). This equals 90-degrees. On the Bell the swashplate tilts down over the nose while the advancing blade is over the lateral axis. The pitch horn leads the blade by 90-degrees. On Aerospatial helicopters the pitch horn leads the blade by 60-degrees and the swashplate tilts down 30-degrees ahead of the forward movement of the cyclic. In each case the designed rig angle or phase angle is 90-degrees. How the blades respond is a result of a lot of contributing factors. (Phase angle shift).
On most helicopters the blades respond 90-degrees after the maximum pitch input or pitch change and this is discounting phase angle shift. If the Robinson the advancing blade is 18-degrees ahead of the lateral axis (as opposed to the Bell blade which is over the lateral axis) when the pitch horn is over the maximum displacement of the swashplate.
Now without going into a lot of technical detail how will the blades respond discounting phase angle shift when the cyclic is displaced forward from the rigged neutral position? Is it 72-degrees or, is it 90-degrees?
My theory does not touch on controllability issues.