Convertiplane

1. A convertiplane ( 1 ) comprising:

a pair of semi-wings ( 3 );

at least two rotors ( 4 ) which may rotate about a first axes (B) and tilt about relative second axes (C) together with said first axes (B) with respect to said semi-wings ( 3 ) between a helicopter mode and an aeroplane mode;

said first axes (B) being, in use, transversal to a longitudinal direction (A) of said convertiplane ( 1 ) in said helicopter mode, and being, in use, substantially parallel to said longitudinal direction (A) in said aeroplane mode;

said semi-wings ( 3 ) comprise relative through openings ( 8 ) within which said relative rotors ( 4 ) may tilt, when said convertiplane ( 1 ) moves, in use, between said helicopter and said aeroplane mode;

said semi-wings ( 3 ) forming a delta-wing;

said convertiplane ( 1 ) further comprising:

a fuselage ( 2 ) from which said semi-wings ( 3 ) project on opposite relative sides; said fuselage ( 2 ) defining a forward end ( 15 ) of said convertiplane ( 1 ), proceeding according to an advancing direction thereof;

a tail ( 7 ) projecting from a backward portion ( 13 ) of said fuselage ( 2 );

each said semi-wing ( 3 ) having:

a respective first leading edge ( 10 ), which comprises a first curved stretch ( 41 ) laterally projecting on a relative opposite side of said fuselage ( 2 ); and

a respective first trailing edge ( 11 ) which is opposite to relative first leading edge ( 10 ), proceeding along said longitudinal direction (A);

characterized in that each said first leading edge ( 10 ) further comprises a second rectilinear stretch ( 42 ) which defines a prolongation of said respective first curved stretch ( 41 ) on the relative opposite side of said fuselage ( 2 );

each said first trailing edge ( 11 ) comprising:

a rectilinear third stretch ( 43 ) extending parallel to relative second axis (C) and on a relative side of said tail ( 7 );

a curved fourth stretch ( 44 ); and

a rectilinear fifth stretch ( 45 ) opposite to said fourth stretch ( 44 ) and inclined relative to said second axis (C);

each said opening ( 8 ) being arranged between said first and third stretch ( 41 , 43 ) of a relative said semi-wing ( 3 ), proceeding along said longitudinal direction (A).

2. The convertiplane of claim 1 , characterized in that said rotors ( 4 ) are fully contained within said openings ( 8 ), when said convertiplane ( 1 ) is operated in said helicopter mode.

3. The convertiplane of claim 1 , characterized by comprising at least two shrouds ( 20 ) which duct relative rotors ( 4 ) and may tilt together with said relative rotors ( 4 ) with respect to said semi-wings ( 3 ).

4. The convertiplane of claim 3 , characterized in that each said shroud ( 20 ) is, in a cross section taken in a plane parallel to first axis (B), shaped as a first airfoil ( 25 );

said first airfoil ( 25 ) comprising:

a second leading edge ( 21 );

a second trailing edge ( 22 );

a chord ( 26 ) connecting said second leading and trailing edges ( 21 , 22 );

said first airfoil ( 25 ) being antisymmetrical relative to said chord ( 26 ).

5. The convertiplane of claim 1 , characterized in that each said rotor ( 4 ) projects on the top of said semi-wing ( 3 ), when said convertiplane ( 1 ) is operated in said aeroplane mode.

6. The convertiplane of claim 4 , wherein the respective first leading edge ( 10 ) of each semi-wing ( 3 ) converges towards said fuselage ( 2 ) and extends at increasing distances from each other, starting from said forward end ( 15 ) and proceeding along said longitudinal direction (A);

wherein the first trailing edge ( 11 ) of each said semi-wing ( 3 ) comprises a substantially rectilinear trailing edge ( 11 ) which is opposite to relative first leading edge ( 10 ), proceeding along said longitudinal direction (A);

each said opening ( 8 ) being arranged between respective portions ( 41 , 45 ) of said first leading edge ( 10 ) and first said trailing edge ( 11 ) of a relative said semi-wing ( 3 ), proceeding along said longitudinal direction (A).

7. The convertiplane according to claim 6 , characterized in that the cross section of said semi-wing ( 3 ) taken in a plane orthogonal to said second axis (C) comprises:

a second airfoil ( 60 ); and

a third airfoil ( 65 ) arranged on the opposite side of said opening ( 8 ) relative to said second airfoil ( 60 );

said second airfoil ( 60 ) being bounded by said first leading edge ( 10 ) and by a third trailing edge ( 29 ; 47 );

said third airfoil ( 65 ) being bounded a third leading edge ( 29 ; 48 ) and by said first trailing edge ( 11 );

said third leading and trailing edges ( 29 ; 47 , 48 ) bounding said opening ( 8 ) on opposite sides relative to said longitudinal direction (A).

8. The convertiplane of claim 6 , characterized by comprising a pair of elevons ( 40 ) movable relative to respective semi-wings ( 3 ) and defined by said first trailing edge ( 11 ), proceeding along said longitudinal direction (A), so that, when said convertiplane ( 1 ) is operated in said helicopter mode, said rotors ( 4 ) generate an airflow against said elevons ( 40 ).

9. The convertiplane of claim 7 , characterized in that said fuselage ( 2 ) is smoothly joined to said semi-wings ( 3 ) and is configured, in a cross section in a plane orthogonal to said second axis (C), as a fourth airfoil ( 35 ).

10. The convertiplane of claim 1 characterized in that each semi-wing ( 3 ) comprises:

a main body ( 17 ); and

a pair of wings ( 18 ) detachably connected to said main body ( 17 ), so that said convertiplane ( 1 ) may be selectively operated in:

a first configuration in which said wings ( 18 ) are connected to said main body ( 17 ); and

a second configuration in which said wings ( 18 ) are released from said main body ( 17 ).

11. The convertiplane of claim 10 , characterized in that said wings ( 18 ) are backward swept.

12. The convertiplane of claim 9 , characterized by comprising:

a common core comprising said semi-wings ( 3 ), said openings ( 8 ) and said rotors ( 4 ); and

a module which can be selectively housed within said fuselage ( 2 );

said module comprising at least one of a cockpit ( 31 ), a payload pallet and/or a sensor assembly.

13. The convertiplane according to claim 1 , characterized in that said rotor ( 4 ) comprises:

a shaft ( 6 );

a plurality of blades ( 27 ) rotatable integrally with said shaft ( 6 ) about said first axis (B) and articulated with respect to said shaft ( 6 ) about respective third axes (G); and

a plurality of actuators ( 100 ) connected to the plurality of blades ( 27 ) for causing the rotation of said blades ( 27 ) about relative third axes (G) and/or for exerting onto respective blades ( 27 ) a force which is directed to suppress the vibration of said blades ( 27 ).

14. The convertiplane of claim 13 , characterized in that said actuators ( 100 ) are electro-mechanical actuators ( 100 ).

15. The convertiplane according to claim 1 , characterized in that said openings ( 8 ) have respective third axes (D), and in that said convertiplane ( 1 ) comprises a centre of gravity which lies on a direction common to said second axes (C) and is arranged at the same distance from said third axes (D).

16. The convertiplane of claim 1 , characterized in that said rotors ( 4 ) generate the lift necessary to the flight of said convertiplane in said helicopter mode.