RVDT, that does look very interesting. This approach has a lot of potential.
Originally Posted by Dave Jackson
You are probably correct in that the servo-flap control of a helicopter may reduce perturbation induced vibrations; in the craft and in the cyclic stick.
Dave, what i mean is that the response is very quick. Then again the longitudinal response of any elevator last fixed wing is not fast (I've wondered about altering main wing AOA or camber (flaps), like a canard).
If response was an issue you could keep a standard blade pitch control mech. The tip servo-flaps would be connected to the mech to compensate for varying pitch moments, like a reflex aerofoil section. This would allow the aerofoil good Cl/Cd characteristics but without the need for hydraulics. The system could be active, using pitch link forces for feedback (although getting power/signal across rotating/static interface would be a challenge).
Heli-Kiwi, that system sounds pretty good with its automatic track. I wonder why it is not more popular? There could be some flap angle feedback in the mech which would explain why the servos appear to have a mind of there own on the ground.