What do you think about this aproach?
Been done by Lockheed as part of the Cheyenne program. Trouble is the wings cause a sizable downforce in hover (Disc area less wing area). Rotor drag is seriously reduced by unloading rotor though, but new developments in blade twist will eventually overcome this problem. For my money X-2 represents the design with highest performance potential.
Pusher props make sense, since they present the minimum aero profile for the rotor hub. The size can also be optimised in terms of minimum parasitic drag.
What about flying in turbulent air whith the rotor unloaded?
Not a problem, since rotor head is rigid. Pilot probably controls roll/pitch through unloaded rotor, at high speed, so there is no risk of rotor strikes. Usually the rotor is not fully unloaded, but the retreating tip AOA is well below stall (ie nearer optimum AOA). Rigid rotor counterrotators can achieve higher speed though.
Worth bearing in mind that the controls will never be as easy as a fixed wing, since pilot is still flying a helicopter control system. Ailerons and elevators effectively control roll/pitch velocity, while rotor systems control pitch/roll acceleration (or more accurately torque, but for small inputs it's effectively acceleration).
Mart