Aircraft with thrust vectoring propulsion assemblies

Patent metadata

Field	Value
Publication number	US-10457390-B2
Application number	US-201916361155-A
Country	US
Kind code	B2
Filing date	Mar 21, 2019
Priority date	Jul 1, 2016
Publication date	Oct 29, 2019
Grant date	Oct 29, 2019

Abstract

An aircraft includes an airframe and a distributed propulsion system including a plurality of propulsion assemblies coupled to the airframe. Each of the propulsion assemblies includes a nacelle, an engine disposed within the nacelle, a proprotor coupled to the engine and a thrust vectoring system. Each thrust vectoring system includes a pivoting plate, a rotary actuator operable to rotate the pivoting plate about a propulsion assembly centerline axis and a linear actuator operable to pivot the pivoting plate about a pivot axis that is normal to the propulsion assembly centerline axis. The engine is mounted on the pivoting plate such that operation of the pivoting plate enables resolution of a thrust vector within a thrust vector cone.

First claim

What is claimed is:

1. A propulsion assembly for an aircraft comprising:
a nacelle;
an engine disposed within the nacelle;
a proprotor coupled to the engine; and
a thrust vectoring system including a pivoting plate, a rotary actuator operable to rotate the pivoting plate about a propulsion assembly centerline axis and a linear actuator operable to pivot the pivoting plate about a pivot axis that is normal to the propulsion assembly centerline axis;
wherein, the engine is mounted on the pivoting plate such that operation of the pivoting plate enables resolution of a thrust vector within a thrust vector cone.

2. The propulsion assembly as recited in claim 1 wherein the engine further comprises an electric motor.

3. The propulsion assembly as recited in claim 2 further comprising a battery disposed within the nacelle and configured to provide electrical power to the electric motor.

4. The propulsion assembly as recited in claim 1 wherein the proprotor further comprises a plurality of proprotor blades.

5. The propulsion assembly as recited in claim 1 wherein the proprotor further comprises a plurality of folding proprotor blades.

6. The propulsion assembly as recited in claim 1 wherein the proprotor further comprises a plurality of fixed pitch proprotor blades.

7. The propulsion assembly as recited in claim 1 wherein the proprotor further comprises a plurality of variable pitch proprotor blades.

8. The propulsion assembly as recited in claim 1 wherein the thrust vector has a maximum angle of about twenty degrees.

9. The propulsion assembly as recited in claim 1 further comprising an electronics node disposed within the nacelle operable to control operations of the propulsion assembly.

10. The propulsion assembly as recited in claim 9 wherein the electronics node further comprises controllers operable to send commands to the engine and the thrust vectoring system.

11. The propulsion assembly as recited in claim 9 wherein the electronics node further comprises sensors operable to monitor parameters associated with the engine and the thrust vectoring system.

12. An aircraft, comprising:
an airframe; and
a distributed propulsion system including a plurality of propulsion assemblies coupled to the airframe, the propulsion assemblies each comprising:
a nacelle;
an engine disposed within the nacelle;
a proprotor coupled to the engine; and
a thrust vectoring system including a pivoting plate, a rotary actuator operable to rotate the pivoting plate about a propulsion assembly centerline axis and a linear actuator operable to pivot the pivoting plate about a pivot axis that is normal to the propulsion assembly centerline axis;
wherein, the engine is mounted on the pivoting plate such that operation of the pivoting plate enables resolution of a thrust vector within a thrust vector cone.

13. The aircraft as recited in claim 12 wherein, for each propulsion assembly, the engine further comprises an electric motor.

14. The aircraft as recited in claim 13 wherein each propulsion assembly further comprising a battery disposed within the nacelle that is configured to provide electrical power to the electric motor.

15. The aircraft as recited in claim 12 wherein, for each propulsion assembly, the thrust vector has a maximum angle of about twenty degrees.

16. The aircraft as recited in claim 12 further comprising a flight control system and wherein each of the propulsion assemblies further comprises an electronics node in communication with the flight control system such that each propulsion assembly is independently controllable by the flight control system.

17. The aircraft as recited in claim 16 wherein, for each propulsion assembly, the electronics node further comprises controllers operable to send commands to the engine and the thrust vectoring system.

18. The aircraft as recited in claim 16 wherein, for each propulsion assembly, the electronics node further comprises sensors operable to monitor parameters associated with the engine and the thrust vectoring system and provide sensor data to the flight control system.

19. The aircraft as recited in claim 12 wherein the airframe further comprises first and second wings having at least two pylons extending therebetween and wherein the distributed propulsion system further comprises at least two propulsion assemblies coupled to the first wing and at least two propulsion assemblies coupled to the second wing.

20. The aircraft as recited in claim 12 wherein the airframe further comprises a vertical takeoff and landing configuration and a forward flight configuration.

Assignees

• Bell Helicopter Textron Inc
• Bell Textron Inc

Inventors

• Mccullough John Richard
• Oldroyd Paul K

Classifications

• B64D1/08

  the articles being load-carrying devices · CPC title

• B64C39/06

  having disc- or ring-shaped wings · CPC title

• B64C29/02

  having its flight directional axis vertical when grounded · CPC title

• B64C11/28

  Collapsible or foldable blades · CPC title

• B64C27/50

  Blades foldable to facilitate stowage of aircraft · CPC title