Aircraft with active aerosurfaces

Patent metadata

Field	Value
Publication number	US-10442522-B2
Application number	US-201715606163-A
Country	US
Kind code	B2
Filing date	May 26, 2017
Priority date	May 26, 2017
Publication date	Oct 15, 2019
Grant date	Oct 15, 2019

Abstract

An aircraft operable to transition between a forward flight mode and a vertical takeoff and landing flight mode. The aircraft includes an airframe having first and second wings. A plurality of propulsion assemblies is attached to the airframe with each of the propulsion assemblies including a nacelle and a tail assembly having at least one active aerosurface. A flight control system is operable to independently control each of the propulsion assemblies. For each of the propulsion assemblies, the tail assembly is rotatable relative to the nacelle such that the active aerosurface has a first orientation generally parallel to the wings and a second orientation generally perpendicular to the wings.

First claim

What is claimed is:

1. An aircraft operable to transition between a forward flight mode and a vertical takeoff and landing flight mode, the aircraft comprising:
an airframe including first and second wings with first and second pylons extending therebetween;
a plurality of propulsion assemblies including two propulsion assemblies coupled to the first wing and two propulsion assemblies coupled to the second wing, each of the propulsion assemblies including a nacelle and a tail assembly having at least one active aerosurface; and
a flight control system operable to independently control each of the propulsion assemblies;
wherein, for each of the propulsion assemblies, the tail assembly is rotatable relative to the nacelle such that the active aerosurface has a first orientation generally parallel to the wings and a second orientation generally perpendicular to the wings.

2. The aircraft as recited in claim 1 wherein, each of the propulsion assemblies further comprises an actuator and wherein, for each of the propulsion assemblies, the actuator is operable to rotate the tail assembly relative to the nacelle.

3. The aircraft as recited in claim 1 wherein, each of the propulsion assemblies further comprises an actuator and wherein, for each of the propulsion assemblies, the actuator is operable to translate the tail assembly relative to the nacelle between a retracted configuration and an extended configuration.

4. The aircraft as recited in claim 1 wherein, in the first orientation, each of the active aerosurface further comprises a horizontal stabilizer.

5. The aircraft as recited in claim 1 wherein, in the first orientation, each of the active aerosurfaces further comprises an elevator.

6. The aircraft as recited in claim 1 wherein, in the first orientation, each of the active aerosurfaces provides pitch control to the aircraft.

7. The aircraft as recited in claim 1 wherein, in the second orientation, each of the active aerosurfaces further comprises a vertical stabilizer.

8. The aircraft as recited in claim 1 wherein, in the second orientation, each of the active aerosurfaces further comprises a rudder.

9. The aircraft as recited in claim 1 wherein, in the second orientation, each of the active aerosurfaces provides yaw control to the aircraft.

10. The aircraft as recited in claim 1 wherein, during vertical takeoff and landing flight maneuvers, each of the active aerosurfaces is in the first orientation.

11. The aircraft as recited in claim 1 wherein, during hover flight maneuvers, each of the active aerosurfaces is in the first orientation.

12. The aircraft as recited in claim 1 wherein, during transitions from vertical takeoff and landing flight maneuvers to forward flight maneuvers, each of the active aerosurfaces is in the first orientation.

13. The aircraft as recited in claim 1 wherein, during transitions from forward flight maneuvers to vertical takeoff and landing flight maneuvers, each of the active aerosurfaces is in the first orientation.

14. The aircraft as recited in claim 1 wherein, during forward flight maneuvers, each of the active aerosurfaces is in the second orientation.

15. An aircraft operable to transition between a forward flight mode and a vertical takeoff and landing flight mode, the aircraft comprising:
an airframe including first and second wings with first and second pylons extending therebetween;
a plurality of propulsion assemblies including two propulsion assemblies coupled to the first wing and two propulsion assemblies coupled to the second wing, each of the propulsion assemblies including a nacelle, a tail assembly having at least one active aerosurface, a first actuator and a second actuator; and
a flight control system operable to independently control each of the propulsion assemblies, the flight control system including an active aerosurface control system operable to control operations of each of the first and second actuators;
wherein, for each of the propulsion assemblies, the first actuator is operable to rotate the tail assembly relative to the nacelle such that the active aerosurface has a first orientation generally parallel to the wings and a second orientation generally perpendicular to the wings; and
wherein, for each of the propulsion assemblies, the second actuator is operable to translate the tail assembly relative to the nacelle between a retracted configuration and an extended configuration.

16. The aircraft as recited in claim 15 wherein, in the first orientation, each of the active aerosurfaces further comprises a horizontal stabilizer operable to provide pitch control to the aircraft.

17. The aircraft as recited in claim 15 wherein, in the first orientation, each of the active aerosurfaces further comprises an elevator operable to provide pitch control to the aircraft.

18. The aircraft as recited in claim 15 wherein, in the second orientation, each of the active aerosurfaces further comprises a vertical stabilizer operable to provide yaw control to the aircraft.

19. The aircraft as recited in claim 15 wherein, in the second orientation, each of the active aerosurfaces further comprises a rudder operable to provide yaw control to the aircraft.

20. The aircraft as recited in claim 15 wherein, during vertical takeoff and landing flight maneuvers, during hover flight maneuvers and during transitions between vertical takeoff and landing flight maneuvers and forward flight maneuvers, each of the active aerosurfaces is in the first orientation and wherein, during forward flight maneuvers, each of the active aerosurfaces is in the second orientation.

Assignees

• Bell Helicopter Textron Inc
• Bell Textron Inc

Inventors

• Oldroyd Paul K
• Mccullough John Richard

Classifications

• B64U70/80

  Vertical take-off or landing, e.g. using rockets (rotorcrafts B64U10/10; VTOL aircraft B64U10/20) · CPC title

• B64C29/02 Primary

  having its flight directional axis vertical when grounded · CPC title

• B64C27/59

  mechanical · CPC title

• B64C5/02 Primary

  Tailplanes · CPC title

• B64C3/385

  Variable incidence wings · CPC title