CONVERTIPLANE

• US 20130026303A1
• Filed: 07/27/2012
• Published: 01/31/2013
• Est. Priority Date: 07/29/2011
• Status: Active Grant

• Current Assignee: Leonardo S.p.A.
• Original Assignee: Agustawestland SP A
• Inventors: Wang, James
• Granted Patent: US 8,991,741 B2
• Time in Patent Office: Days
• US Class Current: 244/7.R
• CPC Class Codes: B64C 11/001 Shrouded propellers
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 3/54 Varying in area
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

There is described a convertiplane comprising: a pair of semi-wings; at least two rotors which may rotate about relative first axes and tilt about relative second axes together with first axis with respect to semi-wings between a helicopter mode and an aeroplane mode; first axis being, in use, transversal to a longitudinal direction of convertiplane in helicopter mode, and being, in use, substantially parallel to longitudinal direction in aeroplane mode; convertiplane further comprises at least two through openings within which said rotor may tilt, when said convertiplane moves, in use, between said helicopter and said aeroplane mode.

Claims

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;

characterized in that 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.

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 first leading edge (21);

a first trailing edge (22);

a chord (26) connecting said first 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 helicopter (1) is operated in said aeroplane mode.

6. ) The convertiplane of claim 1, characterized by 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;

each said semi-wing (3) having a respective second leading edge (10) which converges towards said fuselage (2) and extends at increasing distances from each other, starting from said forward end (15) and proceeding along said advancing direction (A);

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

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

said third leading and trailing edges (29;

47, 48) bounding said opening (8) on opposite sides relative to said 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 second trailing edge (11), proceeding along said 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 6, 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 relative 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).