Patent ID: 8556207

Claim:
An aircraft with counter-rotating sustaining rotors ( 4 , 5 ), comprising: a rotor control head, said rotors operatively connected to the rotor control head; a collective pitch variation control ( 9 ) operatively connected to said rotors ( 4 , 5 ), said collective pitch variation control, via the rotor control head, simultaneously applying an equivalent variation to an incidence of all blades of said rotors ( 4 , 5 ) varying the collective pitch of said rotors, said rotors ( 4 , 5 ) being counter-rotating sustaining coaxial rotors; and an attitude and direction flight control generating aerodynamic forces via sustaining rotor wind from said blades of said rotors ( 4 , 5 ), the aircraft being free of elements for variation of cyclic pitch of the blades of the rotors, the attitude and direction flight control comprising governing surfaces including two governing surfaces ( 2 , 3 ) placed in a back part of the aircraft, and a control element ( 8 ) operatively connected to said two governing surfaces functioning to move said two governing surfaces with respect to each other in order to produce a pitching movement of the whole aircraft, the rotor has a fixed substantially vertical axis, said governing surfaces are substantially constituted by three governing surfaces defined by three ailerons ( 1 , 2 , 3 ), and each of the three ailerons move independently to control the yaw.