Articulated empennage with rudder and elevator

Patent metadata

Field	Value
Publication number	US-11292579-B2
Application number	US-201816141943-A
Country	US
Kind code	B2
Filing date	Sep 25, 2018
Priority date	Sep 25, 2018
Publication date	Apr 5, 2022
Grant date	Apr 5, 2022

Abstract

An aircraft empennage includes a lower vertical fin 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 first and second horizontal stabilizer portions and at least one upper vertical member.

First claim

What is claimed is:

1. An aircraft, comprising:
a fuselage capable of carrying payload, the fuselage having a rear portion; and
an empennage connected to the rear portion of the fuselage, the empennage including a lower vertical fin member, and an upper stabilizer assembly connected to the lower vertical fin member by an articulating mount that allows rotation of the entire upper stabilizer assembly relative to the lower vertical fin member around an axis perpendicular to a plane of symmetry of the fuselage to generate a pitch trim moment acting on the aircraft in a flight mode, wherein the lower vertical fin member has a lower trailing rudder structure, the upper stabilizer assembly having first and second horizontal stabilizer portions and at least a first upper vertical member, the first upper vertical member having a first upper trailing rudder structure, each of the rudder structures being configured to generate a yaw control moment acting on the aircraft,
wherein the lower trailing rudder structure is below the articulating mount, and the first upper trailing rudder structure is above the articulating mount.

2. The aircraft of claim 1 , wherein the first upper trailing rudder structure is directly above the lower trailing rudder structure.

3. The aircraft of claim 1 , wherein the first upper vertical member is connected to a distal end of the first horizontal stabilizer portion, a second upper vertical member being connected to a distal end of the second horizontal stabilizer portion, the first upper trailing rudder structure being connected to a trailing end of the first upper vertical member, and a second upper trailing rudder structure being connected to a trailing end of the second upper vertical member, each of the upper and lower trailing rudder structures being configured to generate a yaw control moment acting on the aircraft.

4. The aircraft of claim 3 , wherein each horizontal stabilizer portion has an adjustable trailing-edge elevator configured to generate a pitch control moment acting on the aircraft.

5. 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, configured to move the upper stabilizer assembly relative to the lower vertical fin member.

6. The aircraft of claim 1 , wherein the articulating mount permits adjustment of the upper stabilizer assembly between a negative incidence angle and a positive incidence angle relative to a longitudinal axis of the fuselage.

7. The aircraft of claim 1 , wherein the articulating mount is contained within a fairing configured to reduce drag.

8. An aircraft, comprising:
a fuselage capable of carrying payload, the fuselage having a rear portion,
a fin assembly including a lower fin portion connected to a first upper fin portion through an articulating mount, and
a first horizontal stabilizer portion connected to a second horizontal stabilizer portion through the articulating mount, wherein the articulating mount permits trim control rotation of the first upper fin portion together with the first and second horizontal stabilizer portions, relative to the lower fin portion, around an axis perpendicular to a plane of symmetry of the fuselage,
wherein the lower fin portion has a first rudder structure positioned below the articulating mount, and the first upper fin portion has a second rudder structure positioned above the articulating mount.

9. The aircraft of claim 8 , wherein the first upper fin portion is located directly above the lower fin portion.

10. The aircraft of claim 8 , wherein the first upper fin portion is connected to a distal end portion of the first horizontal stabilizer portion, a second upper fin portion being connected to a distal end portion of the second horizontal stabilizer portion.

11. The aircraft of claim 8 , wherein each of the fin portions has a trailing-edge control surface configured to generate a yaw control moment acting on the aircraft.

12. The aircraft of claim 8 , wherein the articulating mount is contained within a fairing configured to reduce drag.

13. The aircraft of claim 8 , wherein each horizontal stabilizer portion has an adjustable trailing-edge elevator configured to generate a pitch control moment acting on the aircraft.

14. The aircraft of claim 8 , 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, configured to move the first upper fin portion together with the first and second horizontal stabilizer portions, relative to the lower fin portion.

15. The aircraft of claim 8 , wherein the articulating mount permits adjustment of the first upper fin portion together with the first and second horizontal stabilizer portions, between a negative incidence angle and a positive incidence angle relative to a longitudinal axis of the fuselage.

16. A method of trimming pitch of an aircraft, comprising:
providing an empennage connected to a rear portion of a fuselage, the empennage including a lower vertical fin member, and an upper stabilizer assembly connected to the lower vertical fin member by an articulating mount configured to allow movement of the upper stabilizer assembly relative to the lower vertical fin member to generate a pitch trim moment acting on the aircraft in a flight mode, the lower vertical fin member having a lower trailing rudder structure configured for generating a yaw control moment acting on the aircraft, the upper stabilizer assembly including at least a first horizontal portion and a first vertical portion, the first horizontal portion having a first trailing elevator configured for generating a pitch control moment acting on the aircraft, and the first vertical portion having an upper trailing rudder structure configured for generating a yaw control moment acting on the aircraft, and
rotating the entire upper stabilizer assembly around an axis perpendicular to a plane of symmetry of the aircraft,
wherein the lower trailing rudder structure is below the articulating mount, and the upper trailing rudder structure is above the articulating mount.

17. The method of claim 16 , further comprising:
generating a first yaw control moment acting on the aircraft by moving at least one of: (i) the lower trailing rudder structure, and (ii) the upper trailing rudder structure.

18. The method of claim 17 , further comprising:
generating the first yaw control moment and a second yaw control moment acting on the aircraft by moving both the lower trailing rudder structure and the upper trailing rudder structure.

19. The method of claim 16 , further comprising:
adjusting an orientation of the first trailing elevator and a second trailing elevator of the upper stabilizer assembly, generating first and second pitch control moments acting on the aircraft.

20. The method of claim 16 , further comprising:
adjusting pitch of a longitudinal axis of a fairing containing the articulating mount relative to a longitudinal axis of the fuselage.

21. The method of claim 16 , further comprising:
adjusting an orientation of the first trailing elevator asymmetrically relative to a second trailing elevator of the upper stabilizer assembly.

Assignees

• Boeing Co

Inventors

• Barmichev Sergey
• Sankrithi Mithra

Classifications

• B64C13/24

  Transmitting means · CPC title

• B64C5/16

  about spanwise axes · CPC title

• B64C5/02 Primary

  Tailplanes · CPC title

• B64C9/06

  with two or more independent movements · CPC title

• B64C7/00

  Structures or fairings not otherwise provided for · CPC title