Aircraft door with adjustable support arm hinges

Patent metadata

Field	Value
Publication number	US-12043366-B2
Application number	US-202017619009-A
Country	US
Kind code	B2
Filing date	Jun 12, 2020
Priority date	Jun 15, 2019
Publication date	Jul 23, 2024
Grant date	Jul 23, 2024

Abstract

The invention relates to an aircraft door having a support arm (6) connected to a support forearm (9) by a first pivot connection (7) about a first pivot axis (8), the support forearm (9) being connected to the leaf (5) by a second pivot connection (10) about a second pivot axis (11) parallel to the first pivot axis (8). The support arm (6) is connected to the door frame (4) by two hinges (13, 14) each having a pivot (26, 27) for rotating the support arm (6) about a third pivot axis (12) which is parallel to the first pivot axis (8) and to the second pivot axis (11), this pivot (26, 27) being connected to the door frame (4) by an attachment (22, 23) that is translatably adjustable in two directions (35, 37, 43, 47) orthogonal to one another and orthogonal to the third pivot axis (12).

First claim

The invention claimed is:

1. An aircraft door having:
a leaf ( 5 ) comprising a door structure ( 17 ) to which an external wall ( 18 ) is fixed;
a surround comprising a door frame ( 4 ) intended to be fixed to the fuselage ( 1 ) of the aircraft;
a support arm ( 6 ) of the leaf ( 5 ) having an end mounted pivotably on the door frame ( 4 ), the support arm ( 6 ) being movable between a closed position, in which the leaf ( 5 ) closes the door frame ( 4 ), and an open position, in which the leaf ( 5 ) is released from the door frame ( 4 );
wherein the support arm ( 6 ) is connected to a support forearm ( 9 ) by a first pivot connection ( 7 ), permitting as sole degree of freedom a rotation between the support forearm ( 9 ) and the support arm ( 6 ) about a first pivot axis ( 8 ), the support forearm ( 9 ) being connected to the leaf ( 5 ) by a second pivot connection ( 10 ), permitting as sole degree of freedom a rotation between the leaf ( 5 ) and the support forearm ( 9 ) about a second pivot axis ( 11 ) parallel to the first pivot axis ( 8 );
wherein the support arm ( 6 ) is connected to the door frame ( 4 ) by two hinges ( 13 , 14 ), each of them having a pivot ( 26 , 27 ) for rotation of the support arm ( 6 ) about a third pivot axis ( 12 ), which is parallel to the first pivot axis ( 8 ) and to the second pivot axis ( 11 ), this pivot ( 26 , 27 ) from each hinge ( 13 , 14 ) being connected to the door frame ( 4 ) by a fitting ( 22 , 23 ) that is adjustable in translation in a direction of first translation ( 35 , 43 ) and in a direction of second translation ( 37 , 47 ), these two directions ( 35 , 37 , 43 , 47 ) being orthogonal to each other and orthogonal to the third pivot axis ( 12 );
wherein the rotation pivots ( 26 , 27 ) of the support arm ( 6 ) are adjustable in translation along the third pivot axis ( 12 ); and
wherein the two hinges ( 13 , 14 ) are aligned on the support arm ( 6 ) in such a way that the rotation pivots ( 26 , 27 ) of the support arm ( 6 ) are aligned along the third pivot axis ( 12 ).

2. The aircraft door as claimed in claim 1 , wherein the rotation pivot ( 26 ) of the support arm ( 6 ) of one ( 13 ) of the hinges has a sliding shaft ( 30 ) with which the support arm ( 6 ) is in sliding pivot connection; and in that the rotation pivot ( 27 ) of the support arm ( 6 ) of the other hinge ( 14 ) is connected to the support arm ( 6 ) by a disengageable helical adjustment connection ( 65 ).

3. The aircraft door as claimed in claim 2 , wherein said rotation pivot ( 27 ) of the support arm ( 6 ) of the other hinge ( 14 ) has: a central shaft ( 52 ) mounted on the adjustable fitting ( 23 ) and extending along the third pivot axis ( 12 ); a threaded cylinder ( 53 ) mounted rotatably on the central shaft ( 52 ); an internally threaded sleeve ( 55 ) screwed onto the threaded cylinder ( 53 ) and fixed to the support arm ( 6 ).

4. The aircraft door as claimed in claim 3 , wherein the threaded cylinder ( 53 ) is stopped in rotation by a removable flange ( 57 ) coming into abutment against the support arm ( 6 ).

5. The aircraft door as claimed in claim 1 , wherein the hinges ( 13 , 14 ) each have a base ( 20 , 21 ) fixed to the door frame ( 4 ), the adjustable fitting ( 22 , 23 ) of each hinge ( 13 , 14 ) being mounted in the corresponding base ( 20 , 21 ).

6. The aircraft door as claimed in claim 1 , wherein the adjustable fitting ( 22 , 23 ) of each hinge ( 13 , 14 ) passes through a wall of the door frame ( 4 ).

7. The aircraft door as claimed in claim 5 , wherein the adjustable fitting ( 22 , 23 ) of each hinge ( 13 , 14 ) has a shoe ( 32 , 42 ) mounted in the base ( 20 , 21 ), and a yoke ( 31 , 41 ) connecting the shoe ( 32 , 42 ) to the rotation pivot ( 26 , 27 ) of the support arm ( 6 ).

8. The aircraft door as claimed in claim 7 , wherein the yoke ( 31 , 41 ) of each hinge ( 13 , 14 ) is adjustable in translation with respect to the shoe ( 32 , 42 ), in a direction of first translation ( 35 , 43 ) which is orthogonal to and intersects the third pivot axis ( 12 ).

9. The aircraft door as claimed in claim 7 , wherein the yoke ( 31 , 41 ) of each hinge ( 13 , 14 ) is in helical connection with the shoe ( 32 , 42 ).

10. The aircraft door as claimed in claim 9 , wherein the yoke ( 31 , 41 ) of each hinge ( 13 , 14 ) has: a rotating threaded portion ( 33 , 44 ) mounted in a threaded bore of the shoe ( 32 , 42 ); and an actuation head ( 34 , 45 ) accessible from the base ( 20 , 21 ).

11. The aircraft door as claimed in claim 8 , wherein the shoe ( 32 , 42 ) of each hinge ( 13 , 14 ) is adjustable in translation in a direction of second translation ( 37 , 47 ) which is orthogonal to the third pivot axis ( 12 ) and to the direction of first translation ( 35 , 43 ).

12. The aircraft door as claimed in claim 11 , wherein the shoe ( 32 , 42 ) is mounted on the base ( 20 , 21 ) by way of:
a guide shaft ( 38 , 48 ) extending parallel to the direction of second translation ( 37 , 47 );
an adjustment screw ( 39 , 49 ), extending parallel to the direction of second translation ( 37 , 47 ), which is in pivot connection with the base ( 20 , 21 ) and which is in helical connection with the shoe ( 32 , 42 ).

13. The aircraft door as claimed in claim 1 , further including a pivoting link ( 16 ) and a pivoting front link ( 19 ) connected to each other by a pivot connection, and in that the adjustable fitting ( 23 ) of one ( 14 ) of the hinges has a pivot ( 51 ) for the pivoting link ( 16 ).

14. The aircraft door as claimed in claim 1 , further including a mechanism of opening by lateral escape, all the parts connecting the leaf ( 5 ) to the door frame ( 4 ) being articulated solely by pivot connections along axes parallel to the first pivot axis ( 8 ).

Assignees

• Latecoere

Inventors

• Capron Nicolas
• Dubosc Gregory
• Salles Jean Batiste

Classifications

• E05Y2900/502

  for aircraft or spacecraft · CPC title

• E05D2007/0484

  in a radial direction · CPC title

• E05D15/34

  with wings opening parallel to themselves · CPC title

• E05D3/06

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

• B64C1/1461

  Structures of doors or surrounding frames · CPC title