Articulated empennage with ruddervator

Patent metadata

Field	Value
Publication number	US-11046418-B2
Application number	US-201816141920-A
Country	US
Kind code	B2
Filing date	Sep 25, 2018
Priority date	Sep 25, 2018
Publication date	Jun 29, 2021
Grant date	Jun 29, 2021

Abstract

An aircraft empennage includes a lower vertical member attached to a rear portion of a fuselage, and an upper stabilizer assembly connected to the lower vertical member by an articulating mount configured to allow movement of the upper stabilizer assembly relative to the lower vertical member to adjust pitch trim of the fuselage. The upper stabilizer assembly includes a V-shaped tail member having a pair of angled stabilizer portions, and each angled stabilizer portion has a trailing-edge ruddervator control surface. A rudder may be attached to a trailing edge of the lower vertical member.

First claim

What is claimed is:

1. An aircraft, comprising:
a fuselage capable of carrying payload, the fuselage having a rear portion;
an empennage connected to the rear portion of the fuselage, the empennage including a lower vertical member, and an upper stabilizer assembly connected to the lower vertical member by an articulating mount such that the entire upper stabilizer assembly is rotatable as a unit relative to the lower vertical member around an axis substantially perpendicular to a plane of symmetry of the fuselage to adjust pitch trim of the fuselage in a flight mode, the upper stabilizer assembly including a V-shaped tail member having a pair of angled stabilizer portions both angled upward or downward to collectively form an upwardly facing angle or a downwardly facing angle, respectively, each angled stabilizer portion having a trailing-edge control surface and forming an angle with a horizontal plane of at least 20 degrees; and
a controller enabling independent asymmetric adjustment of the trailing-edge control surfaces generating a first yaw control moment acting on the aircraft.

2. The aircraft of claim 1 , wherein the V-shaped tail member forms the upwardly facing angle.

3. The aircraft of claim 1 , wherein the V-shaped tail member forms the downwardly facing angle.

4. The aircraft of claim 1 , wherein the lower vertical member has a trailing-edge lower rudder for generating at least one of (i) a yaw trim moment acting on the aircraft, and (ii) a second yaw control moment acting on the aircraft.

5. The aircraft of claim 1 , wherein the trailing-edge control surfaces comprise ruddervators.

6. The aircraft of claim 5 , wherein the lower vertical member has a lower rudder, and wherein the controller is programmed to operate the ruddervators in combination with the lower rudder to generate first and second yaw control moments acting on the aircraft.

7. The aircraft of claim 1 , wherein the lower vertical member comprises a lower fin member.

8. The aircraft of claim 1 , further comprising an articulation device including at least one of (i) a jackscrew actuator, (ii) a hydraulic actuator, (iii) an electrohydraulic actuator and an (iv) electromechanical actuator, for moving the entire upper stabilizer assembly relative to the lower vertical member to a commanded orientation.

9. The aircraft of claim 1 , further comprising at least one of (i) a fairing device, and (ii) a wiping surface device configured to reduce aerodynamic drag associated with the combination of the upper stabilizer assembly and the lower vertical member connected by the articulating mount.

10. The aircraft of claim 1 , further comprising a wing attached to the fuselage, the wing being capable of generating aerodynamic lift acting on the aircraft.

11. The aircraft of claim 10 , further comprising a propulsor attached to the fuselage or the wing, the propulsor being capable of generating thrust acting on the aircraft.

12. An aircraft comprising:
a fuselage capable of carrying payload, the fuselage having a rear portion;
an empennage connected to the rear portion of the fuselage, the empennage including a vertical fin member rigidly connected to the fuselage; and
a V-shaped tail portion adjustably mounted to a distal portion of the vertical fin member, the V-shaped tail portion having a pair of angled stabilizer portions both angled upward or downward to collectively form an upwardly facing angle or a downwardly facing angle, respectively, each angled stabilizer portion having a trailing-edge control surface and forming an angle with a horizontal plane of at least 20 degrees, the entire V-shaped tail portion being rotatable as a unit relative to the vertical fin member around an axis substantially perpendicular to a plane of symmetry of the fuselage.

13. The aircraft of claim 12 , wherein the vertical fin member has a trailing rudder, and the V-shaped tail portion has a pair of ruddervators, the trailing rudder and the ruddervators being configured to cooperatively generate yaw control moments acting on the aircraft.

14. The aircraft of claim 13 , wherein the pair of ruddervators are configured to operate asymmetrically.

15. The aircraft of claim 13 , wherein each ruddervator forms an angle of at least 20 degrees relative to a horizontal axis.

16. The aircraft of claim 12 , further comprising an articulation device including at least one of (i) a jackscrew actuator, (ii) a hydraulic actuator, (iii) an electrohydraulic actuator and an (iv) electromechanical actuator, for moving the entire V-shaped tail portion relative to the vertical fin member to a commanded orientation.

17. The aircraft of claim 12 , wherein the V-shaped tail portion is adjustably mounted to the distal portion of the vertical fin member using an articulating mount, further comprising at least one of (i) a fairing device, and (ii) a wiping surface device configured to reduce aerodynamic drag associated with a combination of the vertical fin member and the V-shaped tail portion adjustably mounted to the distal portion of the vertical fin member using the articulating mount.

18. A method of controlling an aircraft, comprising:
trimming pitch of a V-shaped tail portion relative to a lower fin member connected to an end portion of an aircraft, the V-shaped tail portion having a pair of angled stabilizer portions both angled upward or downward to collectively form an upwardly facing angle or a downwardly facing angle, respectively, each angled stabilizer portion having a trailing-edge control surface and forming an angle with a horizontal plane of at least 20 degrees; and
wherein trimming pitch includes rotating the entire V-shaped tail portion relative to the lower fin member around an axis substantially perpendicular to a plane of symmetry of the aircraft.

19. The method of claim 18 , further comprising:
asymmetrically adjusting one or more ruddervators on the V-shaped tail portion to generate a first yaw control moment on the aircraft.

20. The method of claim 19 , further comprising:
adjusting a trailing-edge rudder on the lower fin member to generate a second yaw control moment on the aircraft.

Assignees

• Boeing Co

Inventors

• Barmichev Sergey
• Sankrithi Mithra

Classifications

• B64C5/02 Primary

  Tailplanes · CPC title

• B64C13/24

  Transmitting means · CPC title

• B64C13/16

  actuated automatically, e.g. responsive to gust detectors · CPC title

• B64C13/04

  actuated personally · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title