HYBRID HELICOPTER THAT IS FAST AND HAS LONG RANGE

• US 20100065677A1
• Filed: 03/24/2009
• Published: 03/18/2010
• Est. Priority Date: 03/25/2008
• Status: Active Grant

• Current Assignee: Airbus Helicopters
• Original Assignee: Eurocopter
• Inventors: Ferrier, Jean-Jacques
• Granted Patent: US 8,070,089 B2
• Time in Patent Office: Days
• US Class Current: 244/6
• CPC Class Codes: B64C 2027/8227 comprising more than one rotor
• CPC Class Codes: B64C 2027/8236 including pusher propellers
• CPC Class Codes: B64C 27/26 characterised by provision of fixed wings

Abstract

A hybrid helicopter (1) includes a central fuselage (2) defining a front end (3) and a rear end (4), the hybrid helicopter (1) having a main lift rotor (10), an additional lift surface (20), a mechanical interconnection system (40), and at least one turbine engine (61, 62) for continuously driving the main rotor (10) in rotation. Furthermore, the main rotor (10) is mechanically connected to the mechanical interconnection system (40) by rotary rotor mast (12), and the additional lift surface (20) is arranged at the rear of the hybrid helicopter (1) between the rotor mast (12) and the rear end (4) of the fuselage (2), each end zone (21′, 22′) of the wings (21, 22) of the additional lift surface (20) being provided with a vertical element (23, 24) fitted with a rudder (23′, 24′).

Claims

1. A hybrid helicopter (1) comprising a central fuselage (2) defining a front end (3) and a rear end (4), said hybrid helicopter (1) comprising:

a main lift rotor (10) provided with a plurality of blades (11), arranged above said fuselage;

an additional lift surface (20) provided with first and second wings (21, 22) extending on either side of said fuselage (2) from respective root zones (28, 29) to respective end zones (21′

, 22′

), each wing (21, 22) being provided with a propeller (31, 32);

a mechanical interconnection system (40) between said main rotor (10) and said propellers (31, 32); and

at least one turbine engine (61, 62) for continuously driving said main rotor (10) and said propellers (31, 32) in rotation by meshing with said mechanical system;

wherein said main rotor (10) is mechanically connected to the mechanical interconnection system (40) via a rotary rotor mast (12), said additional lift surface (20) is arranged at the rear of the hybrid helicopter (1) between said rotor mast (12) and said rear end (4) of the fuselage (2), and said hybrid helicopter (1) is provided with a stabilizer surface (50) arranged at the front end (3) of said fuselage (2).

2. A hybrid helicopter according to claim 1, wherein the center of lift of the assembly comprising the wings (21, 22) and the stabilizer surface (50) coincides with the center of lift of said main rotor (10).

3. A hybrid helicopter according to claim 1, wherein said stabilizer surface (50) is provided with first and second stabilizer elements (51, 52) extending on either side of the fuselage (2) at its front end (3).

4. A hybrid helicopter according to claim 1, wherein said stabilizer surface (50) includes at least one horizontal control surface (53, 54).

5. A hybrid helicopter according to claim 1, wherein said stabilizer surface (50) is arranged outside the flow passing through said main rotor (10), a first distance (D1) that separates said stabilizer surface (50) from said rotor mast (12) being greater than or equal to the length (L) of said blades (11).

6. A hybrid helicopter according to claim 1, wherein said stabilizer surface (50) is contained in a first plane (P1) and the additional lift surface (20) is contained in a second plane (P2), said first plane (P1) presenting a third angle (A3) relative to said second plane (P2) in such a manner that the stabilizer surface (50) possesses an angle of incidence that is greater than the angle of incidence of the additional lift surface (20) relative to relative air flow.

7. A hybrid helicopter according to claim 1, wherein each end zone (21′

, 22′

) of said wings (21, 22) of the additional lift surface (20) is provided with a vertical element (23, 24).

8. A hybrid helicopter according to claim 7, wherein each vertical element (23, 24) is fitted with a rudder (23′

, 24′

).

9. A hybrid helicopter according to claim 7, wherein said vertical elements (23, 24) present a first angle (A1) relative to the corresponding wing (21, 22) that is obtuse, the vertical elements (23, 24) forming a negative dihedral directed towards the ground (S) when the hybrid helicopter (1) is on the ground.

10. A hybrid helicopter according to claim 1, wherein said wings (21, 22) are swept back so as to present a second angle (A2) relative to the fuselage (2) and so as to be directed towards the rear end (4) of the fuselage (2).

11. A hybrid helicopter according to claim 1, wherein said propellers (31, 32) are in pusher mode, each propeller (31, 32) being beside the trailing edge (21″

, 22″

) of the corresponding wing (21, 22).

12. A hybrid helicopter according to claim 1, wherein each propeller (31, 32) is arranged at the end zone (21′

, 22′

) of the corresponding wing (21, 22).

13. A hybrid helicopter according to claim 1, wherein each vertical element (23, 24) is provided with a support element (25) for supporting the hybrid helicopter (1) relative to the ground.

14. A hybrid helicopter according to claim 1, wherein the speeds of the rotation of the outlet from said at least one turbine engine (61, 62), of said propeller (31, 32), of said main rotor (10), and of said mechanical interconnection system (40) are mutually proportional, the proportionality ratio being constant regardless of the flying configuration of the hybrid helicopter (1) under normal conditions of operation.