Compound helicopter

• US 9,321,526 B2
• Filed: 07/25/2013
• Issued: 04/26/2016
• Est. Priority Date: 07/27/2012
• Status: Active Grant

• Current Assignee: Airbus Helicopters Deutschland Gmbh (Airbus SE)
• Original Assignee: Airbus Helicopters Deutschland Gmbh (Airbus SE)
• Inventors: Fink, Axel, Weiss, Ambrosius, Winkworth, Andrew
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Giczy, Alexander V
• Application Number:
  US13/950,570
• Publication Number:
  US 20140061367A1
• Time in Patent Office: 1,006 Days
• US Class Current: 1/1
• CPC Class Codes: B64C 27/26 characterised by provision of fixed wings
• CPC Class Codes: B64C 39/068 having multiple wings joined at the tips

Abstract

The invention relates to a compound helicopter comprising a fuselage, at least one engine and a main rotor driven by said at least one engine. At least one pair of fixed wings are mounted in an essentially horizontal plane on a left hand and a right hand side of the fuselage and horizontally oriented propulsion devices are mounted to each of the fixed wings, the fixed wings encompassing each a drive shaft from the at least one engine. Each fixed wing comprises a lower main wing and an upper secondary wing being connected to each other within an interconnection region. The propulsion devices include pusher propellers arranged at the interconnection region and the upper secondary wing houses the drive shaft from the at least one engine.

Claims

1. A compound helicopter comprising:

a fuselage with an upper side, a lower side opposed to the upper side, a left hand side, a right hand side, and a transverse axis extending from the left hand side to the right hand side;

at least one engine disposed on the upper side of the fuselage;

a main rotor mounted to the upper side of the fuselage at the transverse axis, the main rotor being driven by the at least one engine;

a first fixed wing mounted on the left hand side and a second fixed wing mounted on the right hand side of the fuselage; and

a respective longitudinally oriented propulsion device mounted to each of the fixed wings at a respective tip of each of the fixed wings, the fixed wings encompassing encompassing each a respective drive shaft from the at least one engine, wherein;

each fixed wing comprises a lower main wing and an upper secondary;

wing, and the upper secondary wing is anhedral;

the upper secondary wing and the lower main wing of each fixed wing are connected to each other within an interconnection region;

each respective propulsion device is arranged at the respective interconnection region of the respective fixed wing aft of the transverse axis, the propulsion devices including propellers in pusher configuration, the propellers being arranged aft of respective trailing edges of the respective fixed wings; and

and the upper secondary wings house the respective drive shafts from the at least one engine.

2. The compound helicopter according to claim 1, wherein the lower main wing is dihedral.

3. The compound helicopter according to claim 1, wherein the respective drive shafts in the upper secondary wings drive the propulsion devices.

4. The compound helicopter according to claim 1, wherein the upper secondary wing is attached to the upper side of the fuselage and the lower main wing is attached to the lower side of the fuselage.

5. The compound helicopter according to claim 1, wherein the lower main wing has a maximum chord 1.2 to 20 times greater than the maximum chord of the upper secondary wing.

6. The compound helicopter according to claim 1, wherein the lower main wing comprises ailerons.

7. The compound helicopter according to claim 1, wherein the upper secondary wing is straight along an upper secondary wing span with a constant chord or tapered.

8. The compound helicopter according to claim 1, wherein a propulsion device housing is arranged on top of the lower main wing and the first root end of the upper secondary wing is attached to an upper part of the propulsion device housing.

9. The compound helicopter according to claim 1, wherein the upper secondary wing is shaped like a streamlined strut.

10. The compound helicopter according to claim 1, wherein the lower main wing has an aspect ratio between 2 and 15.

11. The compound helicopter according to claim 1, wherein the upper secondary wing is rearward swept in the range of −

10°

to −

45°

relative to the transverse axis.

12. The compound helicopter according to claim 1, wherein the lower main wing has a sweep angle in the range of −

30°

to 30°

.

13. The compound helicopter according to claim 1, wherein the interconnection region comprises a pylon, the pylon connecting the lower main wing to either the upper secondary wing or to a housing of the propulsion device.

14. The compound helicopter according to claim 13, wherein the pylon has an angle in a range between ±

45° and

−

45°

to a vertical axis.

15. The compound helicopter according to claim 1, wherein the lower main wing and the upper secondary wing are attached to the fuselage by hinged joints.

16. A rotorcraft comprising:

a fuselage with a port side, a starboard side, and a transverse axis extending from the port side to the starboard side;

at least one engine;

a main rotor mounted to the fuselage at the transverse axis, the main rotor being driven by the at least one engine;

a first fixed wing coupled to the port side, the first fixed wing including a first lower wing and a first upper wing joining at a first junction, the first junction being spaced from the fuselage;

a second fixed wing coupled to the starboard side, the second fixed wing including a second lower wing and a second upper wing joining at a second junction, the second junction being spaced from the fuselage;

a first propulsion device coupled to the first junction at a tip of the first fixed wing and driven by the at least one engine, the first propulsion device including a first pusher propeller arranged aft of the first fixed wing and aft of the transverse axis; and

a second propulsion device coupled to the second junction at a tip of the second fixed wing and driven by the at least one engine, the second propulsion device including a second pusher propeller arranged aft of the second fixed wing and aft of the transverse axis.

17. The rotorcraft of claim 16, wherein the first lower wing, the first upper wing, the second lower wing, and the second upper wing are aft-swept.

18. The rotorcraft of claim 16, further comprising a first drive shaft retained within the first upper wing and a second drive shaft retained within the second upper wing, wherein the at least one engine is disposed on the fuselage and the first drive shaft and the second drive shaft drivingly couple the at least one engine to the first propulsion device and the second propulsion device, respectively.