Tandem rotor wing and tandem fixed wing aircraft

• US 20060266879A1
• Filed: 05/25/2005
• Published: 11/30/2006
• Est. Priority Date: 05/25/2005
• Status: Active Grant

• Current Assignee: Yahoo! Inc. (Apollo Global Management, Inc.), The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Svoboda, Charles R. Jr.
• Granted Patent: US 7,334,755 B2
• Time in Patent Office: Days
• US Class Current: 244/7.A
• CPC Class Codes: B64C 27/08 with two or more rotors
• CPC Class Codes: B64C 27/24 with rotor blades fixed in flight to act as lifting surfaces
• CPC Class Codes: B64C 39/08 having multiple wings

Abstract

Aircraft comprising an airframe having a fuselage, at least two fixed wing sets. A first fixed wing set of the fixed wing sets is positioned closer to a forward end of the fuselage than a second fixed wing set and the second fixed wing set is positioned closer to the aft end of the fuselage than the first fixed wing set. The aircraft includes a power plant mounted on the airframe and at least two rotor wings rotatably mounted on the airframe. Each rotor wing has a plurality of blades extending outward from a central hub to blade tips. The blade tips of the rotor wings circumscribe respective circles centered on the corresponding central hubs during rotation of the rotor wings and each fixed wing set is located generally below the circumscribed circle of only one of the rotor wings. The aircraft includes a rotation mode and a fixed mode.

Claims

1. Aircraft comprising:

an airframe having a fuselage extending longitudinally between a forward end and an aft end opposite said forward end and at least two fixed wing sets extending laterally from the fuselage;

a power plant mounted on the airframe; and

at least two rotor wings rotatably mounted on the airframe, each rotor wing including a plurality of blades extending outward from a central hub to blade tips;

wherein a first fixed wing set of the fixed wing sets is positioned closer to the forward end of the fuselage than a second fixed wing set of the fixed wing sets and the second fixed wing set is positioned closer to the aft end of the fuselage than the first fixed wing set;

wherein the aircraft has a rotation mode in which at least one of the rotor wings is rotated by the power plant and a fixed mode in which the rotor wings are locked to prevent rotation thereof; and

wherein the blade tips of the rotor wings circumscribe respective circles centered on the corresponding central hubs during rotation of the rotor wings and each fixed wing set is located generally below the circumscribed circle of only one of the rotor wings.

2. Aircraft as set forth in claim 1 wherein each of the fixed wing sets has a chord;

and the fixed wing sets are pivotally mounted on the fuselage for selective movement between a forward flight position in which the respective chord extends generally horizontally and a vertical flight position in which the respective chord extends generally vertically.

3. Aircraft as set forth in claim 1 wherein the rotor wings rotate in different planes.

4. Aircraft as set forth in claim 1 further comprising a phase control system operatively connected to at least one of the rotor wings for avoiding contact between rotor wing blades of different rotor wings during rotation of the rotor wings.

5. Aircraft as set forth in claim 4 wherein said control system includes a mechanical coupling system connecting the rotor wings to each other.

6. Aircraft as set forth in claim 4 wherein said control system includes an automated mechanical breaking system for controlling a rotation speed of at least one of the rotor wings.

7. Aircraft as set forth in claim 4 wherein said control system includes an automated throttle control system for controlling a rotation speed of at least one of the rotor wings.

8. Aircraft as set forth in claim 4 wherein said control system includes at least one spoiler having an active surface positioned on a blade surface of at least one rotor wing blade, said spoiler being movable between a substantially flush position in which the active surface of the spoiler is substantially flush with the blade surface and creates substantially no drag and a fully extended position in which the active surface of the spoiler is angled with respect to the blade surface and creates maximum drag.

9. Aircraft comprising:

an airframe having a fuselage extending longitudinally between a forward end and an aft end opposite the forward end and at least two fixed wing sets extending laterally from the fuselage;

a power plant mounted on the airframe; and

at least two rotor wings rotatably mounted on the airframe;

wherein a first rotor wing of the rotor wings is mounted on the airframe at a first longitudinal position of the fuselage closer to the forward end of the fuselage than a second rotor wing of the rotor wings; and

wherein a first fixed wing set of said fixed wing sets is positioned adjacent said first longitudinal position and a second fixed wing set of said fixed wing sets is positioned adjacent said second longitudinal position.

10. Aircraft as set forth in claim 9 wherein said first fixed wing set is mounted on the fuselage in front of said first longitudinal position.

11. Aircraft as set forth in claim 9 wherein said second fixed wing set is mounted on the fuselage behind said second longitudinal position.

12. A method of flying an aircraft, the aircraft having a fuselage, at least two fixed wing sets extending laterally from the fuselage, and at least two rotor wings rotatably mounted on the fuselage, the method comprising:

selectively providing pitch stability to the aircraft using said fixed wing sets;

selectively providing upward thrust to the aircraft using at least one of said rotor wings; and

actively controlling rotation speed of at least one of the rotor wings when both rotor wings to avoid contact between blades of the respective rotor wings.