Aircraft door opening system

Patent metadata

Field	Value
Publication number	US-11465730-B2
Application number	US-201816771874-A
Country	US
Kind code	B2
Filing date	Dec 13, 2018
Priority date	Dec 19, 2017
Publication date	Oct 11, 2022
Grant date	Oct 11, 2022

Abstract

The invention relates to an opening system ( 10 ) for an auxiliary door ( 20 ) of an airplane in a fuselage ( 30 ), the door and the fuselage having skins in the extension of one another. In one exemplary embodiment, the system ( 10 ) includes a framing lintel ( 11 ) integrated into the fuselage, an upper beam ( 2 S) of the door structure arranged opposite the lintel ( 11 ), and a set of three lever links ( 4 A, 4 B, 4 C). Each link is connected, on the one hand, to the lintel ( 11 ) by a lever articulation ( 5 a, 6 a ) fixed relative to the fuselage ( 30 ) and, on the other hand, to the upper beam ( 2 S) by a lever articulation ( 5 b, 6 b ) mobile with the door ( 20 ), the articulations ( 5 a, 5 b; 6 a, 6 b ) being connected respectively to the lintel ( 11 ) and to the upper beam ( 2 S) by fittings ( 41, 43; 42, 44 ). The set of links includes two types of link mounted alternately, in which the mobile articulation ( 5 b, 6 b ) remains positioned respectively close to the fuselage skin ( 30 ) and further from this skin ( 30 ), the articulations ( 5 a, 5 b; 6 a, 6 b ) of two adjacent levers ( 4 A, 4 B; 4 B, 4 C) forming an evolving quadrilateral.

First claim

The invention claimed is:

1. An Aircraft comprising:
a door opening system; and
a fuselage having a fuselage skin;
the door opening system comprises:
an auxiliary door having a door skin,

the door skin integrated into the fuselage skin;
a lintel integrated into the fuselage skin;
an upper beam located on the door skin and arranged opposite the lintel; and
a set of lever links including a first lever link, a second lever link, and a third lever link extending transversely with respect to the door skin and fuselage skin to form a coupling of the door skin to the lintel,
wherein each lever link is connected, on a first side to said lintel by a fixed articulation fixed relative to the fuselage skin and on a second side to said upper beam by a mobile articulation pivotally mobile with the door skin when open, the fixed and the mobile articulations being formed at the end of the set of lever links and connected respectively to the lintel and to the upper beam by a fixing device, and the first lever link and the second lever link are mounted successive and alternately and the fixed articulation are positioned head to tail, so that the mobile and the fixed articulations of two adjacent first and second lever links form an evolving quadrilateral which controls the kinematics of opening the door skin, maintaining flexibility of articulation between the lintel and the upper beam.

2. The aircraft as claimed in claim 1 , wherein the upper beam has an upper face perpendicular to the door skin, the fitting connecting the mobile articulation of the first and the third lever links to said upper beam and a fixing base extending on the upper face of said upper beam.

3. The aircraft as claimed in claim 1 , wherein the lintel has a lower face perpendicular to the fuselage skin and a front face parallel to the fuselage skin, a fitting connecting the articulations of the first and the second lever links to the lintel and a fixing face that is square on the lower face and on the front face of the lintel.

4. The aircraft as claimed in claim 2 , wherein the upper beam has a front face parallel to the door skin and perpendicular to the upper face of said upper beam, a fitting connecting the articulation, of the second lever link to the upper beam and is fixed on the upper face and on the front face of said upper beam.

5. The aircraft as claimed in claim 3 , wherein the fitting connecting the articulation, of the second lever link to the lintel a has a fixing base extending on the lower face of the lintel.

6. The aircraft as claimed in claim 1 , wherein an insulation panel extends from an end region of the fuselage skin and in front of a zone, the panel pressing against a door seal when the door skin is in a closed position.

7. The aircraft in claim 1 , wherein a mass compensation system is installed in the door skin in extension of the second lever link.

8. The aircraft as claimed in claim 7 , wherein the compensation system comprises at least one jack arranged as an extension of at least one of the first and second lever links.

9. The aircraft as claimed in claim 1 , wherein the fixing device is fixed on the upper beam and connected to the articulations of the first and the third lever links and the fitting; have a form of a gooseneck, wherein the second lever link has a lateral profile with a curved shape facing the upper beam.

10. The aircraft as claimed in claim 1 , wherein a stiffening bar connects, parallel to the lintel, the articulations of the first and the third lever links from the fuselage skin.

Assignees

• Latecoere

Inventors

• Romec Christian
• Othomene Renaud

Classifications

• E05Y2900/502

  for aircraft or spacecraft · CPC title

• B64C1/143 Primary

  of the plug type · CPC title

• B64C1/22

  Other structures integral with fuselages to facilitate loading {, e.g. cargo bays, cranes} · CPC title

• B64C1/1461

  Structures of doors or surrounding frames · CPC title

• E05D7/009

  Elongate hinges, e.g. piano-hinges · CPC title