Rotor wing aircraft having an adjustable tail nozzle

• US 7,395,988 B2
• Filed: 11/02/2005
• Issued: 07/08/2008
• Est. Priority Date: 11/02/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Walliser, Eric W., Richardson, Steven D.
• Primary Examiner(s): Collins; Timothy D.
• Application Number:
  US11/265,655
• Publication Number:
  US 20070095970A1
• Time in Patent Office: 979 Days
• Field of Search: 244/17.19
• US Class Current: 244/17.19
• CPC Class Codes: B64C 15/02 the jets being propulsion jets
• CPC Class Codes: B64C 15/14 the jets being other than main propulsion jets jet flaps B64C9/38
• 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
• CPC Class Codes: B64C 27/26 characterised by provision of fixed wings
• CPC Class Codes: B64C 3/385 Variable incidence wings
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

Aircraft including an airframe having a fuselage extending between a forward end and an aft end and a fixed wing extending laterally from the fuselage. The aircraft includes a power plant mounted on the airframe producing exhaust during operation. The aircraft includes a rotor/wing rotatably mounted on the airframe including a plurality of blades and an adjustable nozzle mounted on the airframe downstream from the power plant exhaust for selectively directing the power plant exhaust to exit the aircraft at a pre-selected angle with respect to the airframe within a range of angles extending from about horizontally rearward to about vertically downward.

Claims

1. An aircraft, comprising:

an airframe having a fuselage extending between a forward end and an aft end and a fixed wing extending laterally from the fuselage;

a power plant operatively coupled to the airframe and producing exhaust during operation thereof;

a rotor/wing rotatably coupled to the airframe and including a plurality of blades;

an adjustable nozzle operatively coupled to the airframe and positioned at the aft end and operatively coupled to the power plant by a primary exhaust duct, the adjustable nozzle being configured to receive an exhaust flow from the power plant via the primary exhaust duct and for selectively directing the power plant exhaust within a range of angles extending from about horizontally rearward to about vertically downward with respect to the fuselage; and

a turbine assembly operatively coupled to the airframe and to the rotor/wing, the turbine assembly being directly coupled to the primary exhaust duct between the power plant and the adjustable nozzle and selectively engageable with the exhaust flow, the turbine assembly including;

a body coupled to the primary exhaust duct and having an inlet configured to receive a drive portion of the exhaust flow from the power plant; and

a drive assembly at least partially disposed within the body and coupled to the rotor/wing, the drive assembly being rotatable within the body about a rotation axis and configured to rotate the rotor/wing when subjected to the exhaust.

2. Aircraft as set forth in claim 1 wherein each of the fixed wings 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 aircraft has a rotation mode wherein the rotor/wing is rotated by the power plant and a fixed mode wherein the rotor/wing is locked to prevent rotor/wing rotation.

4. Aircraft as set forth in claim 1 wherein the turbine assembly is configured such that the drive portion of the exhaust flow is received into the body along an approximately radial direction with respect to the rotation axis, is deflected by the drive assembly, and exits from the body approximately along the rotation axis.

5. Aircraft as set forth in claim 4 wherein the drive assembly includes

a drive shaft projecting upwardly with respect to the fuselage and being connected to said rotor/wing;

and

a turbine blade assembly coupled to the drive shaft and rotatable about a rotation axis that projects along the drive shaft, the turbine blade assembly including a plurality of vanes that provide a rotational force when subject to the exhaust.

6. Aircraft as set forth in claim 5 wherein the rotor/wing is rotatable about the rotation axis, and wherein the body is partially disposed within the primary exhaust duct.

7. Aircraft as set forth in claim 6 further comprising:

a yaw control system mounted on the airframe adjacent to the aft end of the fuselage;

wherein said outlet is in fluid communication with said yaw control system for selectively transferring exhaust to the yaw control system.