Helicopter with counter-rotating coaxial rotors without cyclic variation of pitch, equipped with means for aerodynamic control of attitude and flight path

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.