Systems and methods for operating a door of an aircraft

Patent metadata

Field	Value
Publication number	US-11939040-B2
Application number	US-202217654255-A
Country	US
Kind code	B2
Filing date	Mar 10, 2022
Priority date	Jun 30, 2021
Publication date	Mar 26, 2024
Grant date	Mar 26, 2024

Abstract

A hinge assembly of a system for operating a door of an aircraft includes a bracket secured to a structure of the aircraft. The bracket includes a first forward joint and a first aft joint separated by a first distance along a first line. A forward link is coupled to the first forward joint. An aft link is longer than the forward link, and is coupled to the first aft joint. A door coupler is secured to a door. The door coupler includes a second forward joint and a second aft joint separated by a second distance that is less than the first distance. The second distance is along a second line that is parallel to the first line in a stowed position. The forward link is further coupled to the second forward joint, and the aft link is further coupled to the second aft joint.

First claim

What is claimed is:

1. A hinge assembly of a system for operating a door of an aircraft, the hinge assembly comprising:
a bracket secured to a structure of the aircraft, the bracket including a first forward joint and a first aft joint separated by a first distance along a first line;
a forward link coupled to the first forward joint;
an aft link that is longer than the forward link, the aft link coupled to the first aft joint; and
a door coupler secured to the door, the door coupler including a second forward joint and a second aft joint separated by a second distance that is less than the first distance, wherein the second distance is along a second line that is parallel to the first line in a stowed position, the forward link is further coupled to the second forward joint, and the aft link is further coupled to the second aft joint.

2. The hinge assembly of claim 1 , wherein rotation of the forward link and the aft link causes rotation of the door coupler and the door between the stowed position in which a gap between a forward edge of the door and an outer skin of the aircraft extends over third distance, and an open position in which the gap is less than the third distance.

3. The hinge assembly of claim 2 , further comprising a seal disposed between the outer skin of the aircraft and the door, wherein the seal extends over the gap.

4. The hinge assembly of claim 2 , wherein the third distance is less than or equal to 0.030 inches.

5. The hinge assembly of claim 1 , wherein rotation of the forward link and the aft link causes rotation of the door about a pivot axis that is at or proximate to a forward edge of the door.

6. The hinge assembly of claim 5 , wherein the pivot axis is at an outer mold line of the aircraft.

7. The hinge assembly of claim 1 , wherein the aircraft is a hypersonic aircraft.

8. The hinge assembly of claim 1 , wherein the door coupler is secured to a top surface of the door at a forward edge of the door.

9. The hinge assembly of claim 1 , wherein the second forward joint is forward and below the first forward joint, and wherein the second aft joint is forward and below the first aft joint.

10. A method for providing a hinge assembly of a system for operating a door of an aircraft, the method comprising:
securing a bracket secured to a structure of the aircraft, the bracket including a first forward joint and a first aft joint separated by a first distance along a first line;
coupling a forward link to the first forward joint;
coupling an aft link that is longer than the forward link to the first aft joint;
securing a door coupler to the door, the door coupler including a second forward joint and a second aft joint separated by a second distance that is less than the first distance, wherein the second distance is along a second line that is parallel to the first line in a stowed position;
coupling the forward link to the second forward joint; and
coupling the aft link to the second aft joint.

11. The method of claim 10 , further comprising rotating the forward link and the aft link to rotate the door coupler and the door between the stowed position in which a gap between a forward edge of the door and an outer skin of the aircraft extends over a third distance, and an open position in which the gap is less than the third distance.

12. The method of claim 11 , further comprising disposing a seal between the outer skin of the aircraft and the door, wherein the seal extends over the gap.

13. The method of claim 10 , further comprising rotating the forward link and the aft link to rotate the door about a pivot axis that is at or proximate to a forward edge of the door.

14. The method of claim 13 , wherein the pivot axis is at an outer mold line of the aircraft.

15. The method of claim 10 , wherein said securing the door coupler to the door comprises securing the door coupler to a top surface of the door at a forward edge of the door.

16. The method of claim 10 , wherein the second forward joint is forward and below the first forward joint, and wherein the second aft joint is forward and below the first aft joint.

17. An aircraft comprising:
a system for operating a door, the system comprising a plurality of hinge assemblies, each of the hinge assemblies comprising:
a bracket secured to a structure of the aircraft, the bracket including a first forward joint and a first aft joint separated by a first distance;
a forward link coupled to the first forward joint;
an aft link that is longer than the forward link, the aft link coupled to the first aft joint; and
a door coupler secured to a top surface of the door at a forward edge of the door, the door coupler including a second forward joint and a second aft joint separated by a second distance that is less than the first distance, wherein the second forward joint is forward and below the first forward joint, and wherein the second aft joint is forward and below the first aft joint, the forward link is further coupled to the second forward joint, and the aft link is further coupled to the second aft joint, wherein rotation of the forward link and the aft link causes rotation of the door coupler and the door between a stowed position in which a gap between a forward edge of the door and an outer skin of the aircraft is less than a predetermined distance, wherein the first distance is along a first line, and wherein the second distance is along a second line that is parallel to the first line in the stowed position, and an open position in which the gap is less than the predetermined distance, and wherein rotation of the forward link and the aft link causes rotation of the door about a pivot axis that is at or proximate to a forward edge of the door, and wherein the pivot axis is at an outer mold line of the aircraft; and

a seal disposed between the outer skin of the aircraft and the door, wherein the seal extends over the gap.

18. The aircraft of claim 17 , wherein the predetermined distance is less than or equal to 0.030 inches.

19. The aircraft of claim 17 , wherein the aircraft is a hypersonic aircraft.

20. The method of claim 10 , wherein the aircraft is a hypersonic aircraft.

Assignees

• Boeing Co

Inventors

• Foster John K
• Binkholder Ryan
• Jakubowski Jr Thaddeus

Classifications

• B64C1/1461 Primary

  Structures of doors or surrounding frames · CPC title

• B64C1/38

  Constructions adapted to reduce effects of aerodynamic or other external heating · CPC title

• B64C30/00

  Supersonic type aircraft · CPC title

• B64D1/06

  Bomb releasing; Bomb doors · CPC title