How are pitching and rolling moments transferred from rotor to the body? When a rotorcraft pilot moves pushes on the cyclic control stick, the swashplate tilts so that angle of attack of the retreating blades increase and of the advancing blades decrease, which creates forward pitching moment on the rotor (shifted 90° due to gyroscopic effect).

Now the first reaction is that the blades flap up aft and down forward, tilting the plane of rotation forward. But which is then the dominant effect that makes the helicopter body to follow the pitch?


Is is the blades pulling on the hub due to centrifugal force trying to align it with their own plane of rotation,
or is it that the lift vector tilts with the rotor so its action line no longer passes through the centre of gravity?
The impact of these effects depend on the rotor design.  E.g. a teetering rotor only includes the second effect you mentioned (tilted thrust vector), the 1st effect is absent.  The first effect you mentioned increases as the "flap hinge" is moved away from the hub, giving more control force utilizing CF.  You may be interested to know there's typically a 3rd effect - if the blades are restrained from flapping freely (in the simplest case a spring) that restraint creates a pitch moment about the hub which also pitches the aircraft.   Each of these is discussed here.