Dual-flight mode tandem rotor wing

• US 20040056144A1
• Filed: 09/24/2002
• Published: 03/25/2004
• Est. Priority Date: 09/24/2002
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Bass, Steven M., Mitchell, Clark A.
• Granted Patent: US 6,789,764 B2
• Time in Patent Office: Days
• US Class Current: 244/10
• CPC Class Codes: B64C 27/08 with two or more rotors
• CPC Class Codes: B64C 27/18 the means being jet-reaction apparatus
• CPC Class Codes: B64C 27/24 with rotor blades fixed in flight to act as lifting surfaces

Abstract

A vertical takeoff and landing aircraft (10) is provided including an aircraft fuselage (12). A plurality of hubs (20) are mechanically coupled to the fuselage (12) and are rotated by at least one engine (22). A plurality of tandem rotor/wings (14) are mechanically coupled to the plurality of hubs (20) and propel and lift the aircraft fuselage (12). A transitional lift wing (16) is mechanically coupled to the fuselage (12) and enables lift on the fuselage (12) during off-loading lift of the plurality of tandem rotor/wings (14). A main controller (24) is coupled to the plurality of tandem rotor/wings (14) and switches the plurality of tandem rotor/wings (14) between a vertical lift mode and a fixed wing mode. A method of performing the same is also provided.

Claims

1. A vertical takeoff and landing aircraft comprising:

an aircraft fuselage;

a plurality of hubs mechanically coupled to said fuselage and rotated by at least one engine;

a plurality of tandem rotor/wings mechanically coupled to said plurality of hubs and propelling and lifting said aircraft fuselage;

at least one transitional lift wing mechanically coupled to said fuselage and enabling lift of said aircraft fuselage during off-loading lift of said plurality of tandem rotor/wings; and

a main controller coupled to said plurality of tandem rotor/wings and switching said plurality of tandem rotor/wings between a vertical lift mode and a fixed wing mode.

2. An aircraft as in claim 1 further comprising a plurality of fixed pylons coupled between said fuselage and said plurality of hubs.

3. An aircraft as in claim 1 wherein said at least one transitional lift wing is mechanically coupled between said plurality of tandem rotor/wings to said fuselage.

4. An aircraft as in claim 1 wherein said plurality of tandem rotor/wing comprise at least one leading or trailing edge device selected from at least one of a flap, a slat, a flaperon, an aileron, and a split aileron.

5. An aircraft as in claim 1 wherein said at least one transitional lift wing comprises at least one leading or trailing edge device selected from at least one of a flap, a slat, a flaperon, an aileron, and a split aileron.

6. An aircraft as in claim 1 wherein said plurality of tandem rotor/wings rotate during said vertical lift mode and are fixed during said fixed wing mode.

7. An aircraft as in claim 1 wherein said plurality of tandem rotor/wings comprise a plurality of blades.

8. An aircraft as in claim 7 wherein said plurality of blades comprise at least one flow duct.

9. An aircraft as in claim 8 wherein said at least one flow duct serves as an exhaust transport between said at least one engine and at least one exit nozzle during said vertical lift mode.

10. An aircraft as in claim 8 wherein said at least one flow duct is closed during said fixed wing mode and exhaust gases are diverted from entering said plurality of tandem rotor/wings.

11. An aircraft as in claim 8 wherein exhaust gases from said at least one engine are combined and distributed to said at least one flow duct.

12. An aircraft as in claim 7 further comprising hydraulic actuators coupled to and adjusting pitch of said plurality of blades.

13. An aircraft as in claim 12 further comprising at least one pitch altering device coupled to said plurality of blades and said hydraulic actuators adjusting pitch of said plurality of blades.

14. An aircraft as in claim 13 wherein said at least one pitch altering devices is selected from at least one of a feathering hinge, a swashplate, and a blade actuator.

15. An aircraft as in claim 12 wherein said hydraulic actuators are coupled to said plurality of hubs within a pylon fairing.

16. An aircraft as in claim 1 further comprising a synchronization shaft coupling said plurality of tandem rotor/wings.

17. An aircraft as in claim 1 wherein said at least one engine produces exhaust gases, said exhaust gases are combined and directed to and cause a second tandem rotor/wing to rotate, and further comprising a driveshaft mechanically coupling said first tandem rotor/wing to a second tandem rotor/wing, said driveshaft rotating said first tandem rotor/wing in response to rotation of said second tandem rotor/wing.

18. An aircraft as in claim 1 wherein said plurality of hubs are gimbaled.

19. An aircraft as in claim 1 wherein said plurality of hubs have a rigid rotor/wing configuration.

20. An aircraft as in claim 1 wherein said plurality of tandem rotor/wings are approximately symmetrical in shape.

21. An aircraft as in claim 1 wherein said plurality of tandem rotor/wings comprise at least one rotor/wing shape altering feature.

22. An aircraft as in claim 1 where in a cross-section of said plurality of tandem rotor/wings is approximately elliptical in shape.

23. A method of propelling and lifting an aircraft comprising:

(A) operating in a vertical lift mode to generate vertical lift on an aircraft fuselage comprising;

rotating a plurality of tandem rotor/wings; and

(B) switching between a vertical lift mode and a fixed wing mode comprising;

off-loading lift of said plurality of tandem rotor/wings;

enabling lift of said aircraft fuselage during said off-loading; and

laterally fixing said plurality of tandem rotor/wings.

24. A vertical takeoff and landing aircraft comprising:

an aircraft fuselage;

a plurality of hubs mechanically coupled to said fuselage and rotated by at least one engine;

a plurality of tandem rotor/wings mechanically coupled to said plurality of hubs and propelling and lifting said aircraft fuselage, said plurality of tandem rotor/wings rotate during a vertical lift mode and are fixed during a fixed wing mode;

at least one transitional lift wing mechanically coupled to said fuselage and between said plurality of tandem rotor/wings and enabling lift of said aircraft fuselage during off-loading lift of said plurality of tandem rotor/wings; and

a main controller coupled to said plurality of tandem rotor/wings and switching said plurality of tandem rotor/wings between said vertical lift mode and said fixed wing mode.