Rotary-wing and fixed-wing aircraft

1. An aircraft provided with a fuselage extending along a roll axis (AXR) from a front end to a rear end, and along a pitching axis (AXT) from a first side to a second side, the aircraft having a rotary wing above the fuselage and a fixed wing, the aircraft having a control system for controlling the pitch of the blades of the rotary wings, the rotary wing being above both the fuselage and the fixed wing, said fixed wing being made up of at least one wing comprising:

a first half-wing extending parallel to the pitching axis from said first side, and

a second half-wing extending parallel to the pitching axis from said second side,

wherein each half-wing is provided with a top lift portion and a bottom lift portion, said bottom lift portion of a half-wing being arranged in the wake (S) of the top lift portion of that half-wing, the wake (S) being generated by a stream of air (F) coming from said rotary wing and impacting against the top face of the top lift portion when said aircraft is hovering,

wherein each top lift portion extends from a top proximal end arranged against the fuselage towards a top distal end, each bottom lift portion extending from a bottom proximal end in the proximity of the fuselage to a bottom distal end remote from said fuselage, with each top distal end being connected to a bottom distal end, and

wherein each top distal end is secured and fastened directly to a bottom distal end.

2. An aircraft according to claim 1 , wherein said at least one wing is a discontinuous wing, the first top proximal end of the first half-wing being fastened to the first side of the fuselage, the second top proximal end of the second half-wing being fastened to the second side of the fuselage.

3. An aircraft according to claim 1 , wherein said at least one wing is a continuous wing, the first top proximal end of the first half-wing being fastened to the second top proximal end of the second half-wing by a through portion of the at least one wing that passes through the fuselage parallel to the pitching axis.

4. An aircraft according to claim 1 , wherein the first bottom proximal end of the first half-wing is fastened to the first side of the fuselage, the second bottom proximal end of the second half-wing being fastened to the second side of the fuselage.

5. An aircraft according to claim 1 , wherein the first bottom proximal end of the first half-wing is fastened to the second bottom proximal end of the second half-wing by an airfoil member of the at least one wing, said fuselage being above said airfoil member.

6. An aircraft according to claim 1 , wherein said at least one wing includes at least one external strut for fastening each half-wing to the fuselage.

7. An aircraft according to claim 1 , wherein said fixed wing is made up of two half-wing pairs.

8. An aircraft according to claim 1 , wherein at least one half-wing carries a piece of equipment.

9. An aircraft according to claim 1 , wherein said aircraft is provided with a horizontal tail plane.

10. An aircraft comprising:

a fuselage extending along a roll axis (AXR) from a front end to a rear end, and along a pitching axis (AXT) from a first side to a second side;

a rotary wing above the fuselage,

a control system for controlling the pitch of the blades of the rotary wing, and

a fixed wing comprising:

a first half-wing extending parallel to the pitching axis from said first side and,

a second half-wing extending parallel to the pitching axis from said second side,

at least one strut for fastening each half-wing to the fuselage, and

an airfoil member positioned below said fuselage, the airfoil member fastening the first bottom proximal end of the first half-wing to the second bottom proximal end of the second half-wing,

wherein each half-wing is provided with a top lift portion and a bottom lift portion, said bottom lift portion of a half-wing being arranged in the wake (S) of the top lift portion of that half-wing, the wake (S) being generated by a stream of air (F) coming from said rotary wing and impacting against the top face of the top lift portion when said aircraft is hovering, wherein each top lift portion extends from a top proximal end arranged against the fuselage towards a top distal end, each bottom lift portion extending from a bottom proximal end in the proximity of the fuselage to a bottom distal end remote from said fuselage, with each top distal end being secured and fastened directly to a bottom distal end;

wherein the rotary wing is above both the fuselage and the fixed wing.

11. An aircraft comprising:

a fuselage extending along a roll axis (AXR) from a front end to a rear end, and along a pitching axis (AXT) from a first side to a second side;

a rotary wing supported by and above the fuselage,

a control system for controlling the pitch of the blades of the rotary wing, and

a fixed wing comprising:

a first closed half-wing extending parallel to the pitching axis from said first side and,

a second closed half-wing extending parallel to the pitching axis from said second side;

wherein each half-wing is provided with a top lift portion and a bottom lift portion positioned directly beneath the top lift portion, said bottom lift portion of a half-wing being arranged in the wake (S) of the top lift portion of that half-wing, the wake (S) being generated by a stream of air (F) coming from said rotary wing and impacting against the top face of the top lift portion when said aircraft is hovering, wherein each top lift portion extends from a top proximal end arranged against the fuselage towards a top distal end, each bottom lift portion extending from a bottom proximal end in the proximity of the fuselage to a bottom distal end remote from said fuselage, with each top distal end is secured and fastened directly to a bottom distal end; and

wherein the rotary wing is above both the fuselage and the fixed wing.

12. The aircraft of claim 11 wherein the fixed wing is a first fixed wing, the aircraft further comprising a second fixed wing spaced apart from the first fixed wing along a longitudinal axis of the aircraft, the second fixed wing comprising:

a third closed half-wing extending parallel to the pitching axis from said first side and,

a fourth closed half-wing extending parallel to the pitching axis from said second side;

wherein each half-wing is provided with a top lift portion and a bottom lift portion positioned directly beneath the top lift portion, said bottom lift portion of a half-wing being arranged in the wake (S) of the top lift portion of that half-wing, the wake (S) being generated by a stream of air (F) coming from said rotary wing and impacting against the top face of the top lift portion when said aircraft has a forward speed slower than a predetermined threshold, wherein each top lift portion extends from a top proximal end arranged against the fuselage towards a top distal end, each bottom lift portion extending from a bottom proximal end in the proximity of the fuselage to a bottom distal end remote from said fuselage, with each top distal end is secured and fastened directly to a bottom distal end; and

wherein the rotary wing is above both the fuselage and the fixed wing.

13. The aircraft of claim 11 wherein the top lift portion and bottom lift portion of each of the half-wings are curved towards one another.

14. The aircraft of claim 11 wherein the top lift portion and bottom lift portion of each of the half-wings are generally planar.

15. The aircraft of claim 11 further comprising:

an airfoil member of the fixed wing, the airfoil member fastening the first bottom proximal end of the first half-wing to the second bottom proximal end of the second half-wing, wherein the first bottom proximal end of the first half-wing, the second bottom proximal end of the second half-wing, and the airfoil member are spaced apart and disconnected from the fuselage; and

first and second external struts, each strut connected the fuselage to the top face of a respective bottom lift portion of a half-wing.

16. The aircraft of claim 11 wherein the first and second half wings are in a fixed position on the fuselage.

17. The aircraft of claim 11 further comprising at least one of a propulsive unit and a ferrying tank supported by one of the half-wings and positioned between the top and bottom lift portions.