Rotor/wing aircraft including vectorable nozzle

• US 10,065,735 B2
• Filed: 12/13/2017
• Issued: 09/04/2018
• Est. Priority Date: 11/02/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Richardson, Steven D.
• Primary Examiner(s): Xavier, Valentina
• Application Number:
  US15/840,979
• Publication Number:
  US 20180170536A1
• Time in Patent Office: 265 Days
• 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 27/82 characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
• CPC Class Codes: B64C 3/385 Variable incidence wings
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

A method of operating an aircraft having a rotor/wing assembly and a nozzle comprises vectoring the nozzle into a position for creating vertical thrust, and using the rotor/wing assembly and the nozzle together to create vertical thrust during a rotary mode of operation.

Claims

1. A method of operating an aircraft having a rotor/wing assembly and a nozzle, the method comprising:

vectoring the nozzle into a position for creating vertical thrust;

using the rotor/wing assembly and the nozzle together to create vertical thrust during a rotary mode of operation, wherein the aircraft includes a turbine engine to produce an exhaust flow, wherein the rotor/wing assembly is configured to extract work from the exhaust flow and then direct the exhaust flow to the nozzle during the rotary mode of operation, wherein the rotor/wing assembly includes a rotor/wing and a turbine to drive the rotor/wing during the rotary mode of operation, the turbine including an inlet, a valve disposed in the inlet, an outlet, a vortical chamber and a chamber outlet, the inlet to receive the exhaust flow from the turbine engine, and wherein the aircraft includes a conduit fluidly coupling the outlet to the nozzle; and

bypassing the rotor/wing assembly and using the nozzle to create forward thrust during a fixed mode of operation by operating the valve to direct the exhaust flow from the inlet to the outlet of the turbine.

2. The method of claim 1, wherein the position is a downward position, and wherein using the nozzle to create forward thrust during the fixed mode of operation includes vectoring the nozzle into an aftward position.

3. The method of claim 2, wherein the nozzle is disposed at an aft end of the aircraft.

4. The method of claim 1, wherein using the rotor/wing assembly to create vertical thrust during the rotary mode of operation includes operating the valve to direct the exhaust flow from the inlet, through the vortical chamber, to the chamber outlet.

5. The method of claim 4, wherein the conduit is a first conduit, and wherein the aircraft further includes a second conduit fluidly coupling the chamber outlet to the first conduit.

6. The method of claim 5, further including directing the exhaust flow from the second conduit to the first conduit during the rotary mode of operation, thereby providing the exhaust flow to the nozzle during the rotary mode of operation.

7. The method of claim 6, wherein the valve is a first valve, and wherein directing the exhaust flow from the second conduit to the first conduit includes operating a second valve disposed at a junction of the first conduit and the second conduit.

8. The method of claim 7, further including diverting a portion of the exhaust flow from the first conduit using the second valve to provide yaw control during the fixed mode of operation.

9. The method of claim 4, wherein the turbine is a radial inflow turbine.

10. The method of claim 5, further including diverting a portion of the exhaust flow from the second conduit to a yaw control system to provide yaw control during the rotary mode of operation.

11. The method of claim 10, wherein the yaw control system includes a left lateral outlet and a right lateral outlet.

12. The method of claim 11, wherein the valve is a first valve, further including operating a second valve to divert the exhaust flow to at least one of the left lateral outlet or right left lateral outlet.

13. The method of claim 11, wherein the left and right lateral outlets are near an aft end of the aircraft.

14. The method of claim 1, further including locking the rotor/wing to prevent rotation of the rotor/wing during the fixed mode of operation.

15. The method of claim 1, wherein the aircraft includes canards, and wherein the method further includes pivoting the canards during conversion between the fixed and rotary modes of operation.

16. The method of claim 1, wherein the aircraft includes a tail assembly, and wherein the method further includes pivoting the tail assembly during conversion between the fixed and rotary modes of operation.

17. The method of claim 1, further including independently controlling an amount of vertical thrust produced by each of the rotor/wing assembly and the nozzle.