Systems and methods for linkage controlling access panel on commercial aircraft

Patent metadata

Field	Value
Publication number	US-10538303-B2
Application number	US-201715638337-A
Country	US
Kind code	B2
Filing date	Jun 29, 2017
Priority date	Jun 29, 2017
Publication date	Jan 21, 2020
Grant date	Jan 21, 2020

Abstract

Various techniques are provided for a high clearance hinge linkage. In one example, a system includes a hinge linkage configured to couple to an aircraft beam to an aircraft panel. The hinge linkage includes an aircraft beam fitting configured to couple to a web of the aircraft beam and be disposed between an upper flange and a lower flange of the aircraft beam, an aircraft panel fitting coupled to the aircraft panel, and a plurality of links. The plurality of links couple the aircraft beam fitting to the aircraft panel fitting and are configured to articulate to move the aircraft panel between at least a closed position and an open position. In certain examples, an edge of the aircraft panel is substantially aligned with a portion of the aircraft beam web in the closed position. Additional systems and related methods are also provided.

First claim

What is claimed is:

1. A system comprising:
a hinge linkage configured to couple an aircraft beam to an aircraft panel, the hinge linkage comprising:
an aircraft beam fitting configured to couple to a web of the aircraft beam and be disposed between an upper flange and a lower flange of the aircraft beam;
an aircraft panel fitting coupled to the aircraft panel;
a plurality of links coupling the aircraft beam fitting to the aircraft panel fitting and configured to articulate to move the aircraft panel between at least a closed position and an open position, wherein an edge of the aircraft panel is substantially aligned with a portion of the aircraft beam web in the closed position; and
the plurality of links comprises first and second joint assemblies each comprising associated first and second joint hold open locations, the first and second joint hold open locations configured to align with each other when the aircraft panel is moved to the open position to receive a locking pin to lock the first and second joint assemblies together and hold the aircraft panel in the open position.

2. The system of claim 1 , wherein:
the aircraft beam fitting comprises an upper aircraft beam attachment point and a lower aircraft beam attachment point;
the aircraft panel fitting comprises a forward aircraft panel attachment point and a rearward aircraft panel attachment point; and
the first joint assembly comprises an upper aircraft beam link coupled to the upper aircraft beam attachment point and a forward aircraft panel link coupled to the upper aircraft beam link and the forward aircraft panel attachment point, and
the second joint assembly comprises a lower aircraft beam link coupled to the lower aircraft beam attachment point and a rearward aircraft panel link coupled to the lower aircraft beam link and the rearward aircraft panel attachment point.

3. The system of claim 2 , wherein the lower aircraft beam link has a longer effective distance than the upper aircraft beam link and the forward aircraft panel link has a longer effective distance than the rearward aircraft panel link.

4. The system of claim 2 , wherein the forward aircraft panel link is further coupled to the lower aircraft beam link to further define a travel path of the aircraft panel between the closed position and the open position.

5. The system of claim 1 , further comprising an over travel stop configured to contact the hinge linkage when the aircraft panel is moved to an over travel position.

6. The system of claim 1 , wherein a virtual hinge point location of the plurality of links is configured so that a swept volume of a travel path of the aircraft panel, moving between the closed position and the open position, does not intersect with the aircraft beam.

7. The system of claim 1 , wherein the aircraft panel comprises a plurality of sides, one or more of the hinge linkages are disposed on a first side of the aircraft panel, and further comprising a plurality of latches, wherein at least one of the plurality of latches are disposed on each of the plurality of sides of the aircraft panel.

8. The system of claim 1 , wherein the system is an aircraft, and wherein the aircraft comprises the aircraft beam and the aircraft panel.

9. The system of claim 1 , further comprising:
a wing;
a fuselage; and
an aircraft component disposed within the wing and/or the fuselage, wherein the aircraft panel is disposed on at least a portion of the wing and/or the fuselage, and wherein the aircraft panel covers at least a portion of the aircraft component in the closed position.

10. The system of claim 1 , further comprising the locking pin.

11. A method comprising:
moving an aircraft panel from a closed position to an open position, wherein movement of the aircraft panel from the closed position to the open position is controlled by a hinge linkage configured to couple an aircraft beam to an aircraft panel, the hinge linkage comprising:
an aircraft beam fitting configured to couple to a web of the aircraft beam and be disposed between an upper flange and a lower flange of the aircraft beam;
an aircraft panel fitting coupled to the aircraft panel;
a plurality of links coupling the aircraft beam fitting to the aircraft panel fitting and configured to articulate to move the aircraft panel between at least a closed position and an open position, wherein an edge of the aircraft panel is substantially aligned with a portion of the aircraft beam web in the closed position; and
the plurality of links comprises first and second joint assemblies each comprising associated first and second joint hold open locations, the first and second joint hold open locations configured to align with each other when the aircraft panel is moved to the open position to receive a locking pin to lock the first and second joint assemblies together and hold the aircraft panel in the open position.

12. The method of claim 11 , wherein:
the aircraft beam fitting comprises an upper aircraft beam attachment point and a lower aircraft beam attachment point;
the aircraft panel fitting comprises a forward aircraft panel attachment point and a rearward aircraft panel attachment point; and
the first joint assembly comprises an upper aircraft beam link coupled to the upper aircraft beam attachment point and a forward aircraft panel link coupled to the upper aircraft beam link and the forward aircraft panel attachment point, and
the second joint assembly comprises a lower aircraft beam link coupled to the lower aircraft beam attachment point and a rearward aircraft panel link coupled to the lower aircraft beam link and the rearward aircraft panel attachment point.

13. The method of claim 12 , wherein the lower aircraft beam link has a longer effective distance than the upper aircraft beam link and the forward aircraft panel link has a longer effective distance than the rearward aircraft panel link.

14. The method of claim 12 , wherein the forward aircraft panel link is further coupled to the lower aircraft beam link to further define a travel path of the aircraft panel between the closed position and the open position.

15. The method of claim 11 , further comprising:
inserting the locking pin into the first and second joint hold open locations to hold the aircraft panel in the open position.

16. The method of claim 11 , further comprising moving the aircraft panel to an over travel position, wherein, in the over travel position, an over travel stop contacts the hinge linkage.

17. The method of claim 11 , wherein a virtual hinge point location of the plurality of links is configured so that a swept volume of a travel path of the aircraft panel, moving between the closed position and the open position, does not intersect with the aircraft beam.

18. The method of claim 11 , further comprising:
disengaging a plurality of latches before moving the aircraft panel from the closed position, wherein the aircraft panel comprises a plurality of sides, one or more of the hinge linkages are disposed on a first side of the aircraft panel, wherein the aircraft panel comprises the plurality of latches, and wherein at least one of the plurality of latches are disposed on each of the plurality of sides of the aircraft panel.

19. The method of claim 11 , wherein the aircraft panel and the aircraft beam is disposed on an aircraft.

20. The method of claim 11 , wherein the aircraft panel is disposed on at least a portion of a wing and/or a fuselage, and wherein the aircraft panel covers at least a portion of an air

Assignees

• Boeing Co

Inventors

• Kijak Mark D
• Winkelmann Timothy J

Classifications

• B64C1/1446 Primary

  Inspection hatches (for engine cowls B64D29/08) · CPC title

• E05D15/04

  with arms fixed on the wing pivoting about an axis outside of the wing · CPC title

• E05D15/48

  allowing alternative movements ({E05D15/0604 takes precedence } ; for vertically-sliding wings E05D15/22) · CPC title

• E05Y2900/502

  for aircraft or spacecraft · CPC title

• E05D3/06

  with two or more pins (E05D7/08 takes precedence) · CPC title