Aircraft including a support deployable outside the fuselage

Patent metadata

Field	Value
Publication number	US-9745044-B2
Application number	US-201514680346-A
Country	US
Kind code	B2
Filing date	Apr 7, 2015
Priority date	Apr 8, 2014
Publication date	Aug 29, 2017
Grant date	Aug 29, 2017

Abstract

An aircraft including a fuselage with a skin in which is made an opening, the skin delimiting the interior and the exterior of the fuselage. A closure panel is mobile between a closed position in which the panel covers the opening and an open position in which the closure panel uncovers the opening. A support including a base is fastened to the fuselage. At least one bar and an articulation between the bar and the base allow the bar to occupy a position retracted inside the fuselage and a deployed position outside the fuselage. The articulation is a pivoting connection.

First claim

The invention claimed is:

1. An aircraft comprising:
a fuselage with a skin in which is made an opening, the skin delimiting the interior and the exterior of the fuselage,
a closure panel mobile between a closed position and an open position in which said closure panel uncovers the opening and
a support including a base fastened to the fuselage,
at least one bar and an articulation between said at least one bar and said base allowing the at least one bar to occupy a position retracted inside the fuselage and a position deployed outside the fuselage,
wherein the articulation is a pivoting connection, wherein said at least one bar is joined by said pivoting connection and wherein said at least one bar is free from connection to the closure panel when in the deployed position.

2. The aircraft as claimed in claim 1 , wherein the pivoting connection has a pivot axis parallel to an exterior surface of the fuselage.

3. The aircraft as claimed in claim 1 , wherein the support is disposed in a corner of the opening.

4. The aircraft as claimed in claim 1 , wherein the support includes a locking system configured to occupy a locked state in which it immobilizes the at least one bar in rotation and an unlocked state in which it allows the rotation of the at least one bar.

5. The aircraft as claimed in claim 4 , wherein the at least one bar includes a head connected to the base by the pivot, said head including at least one notch for the deployed position and wherein the locking system includes a lever with a projecting shape that cooperates with the notch of the head when the at least one bar is in the deployed position, said lever being mobile between a position away from the head of the at least one bar that corresponds to the unlocked state and a position in contact with the head of the at least one bar.

6. The aircraft as claimed in claim 5 , wherein the head includes at least one stop for the retracted position.

7. The aircraft as claimed in claim 5 , wherein the locking system includes a return spring urging the lever into contact with the head of the at least one bar.

8. The aircraft as claimed in claim 5 , wherein the lever is connected to the base by a hinge pin parallel to the pivot axis of the at least one bar and wherein the lever includes a lug with a first portion that extends in a direction parallel to the hinge pin, an intermediate portion that extends in a plane perpendicular to the hinge pin and an end that extends in a plane parallel to the hinge pin.

9. The aircraft as claimed in claim 1 , wherein the pivot axis of the at least one bar is between an exterior surface and an interior surface of the fuselage.

10. The aircraft as claimed in claim 9 , wherein the at least one bar comprises:
a head connected to the base by the pivot,
a rectilinear first portion,
a cranked second portion and
a rectilinear third portion,
the rectilinear first portion and the cranked second portion of the at least one bar having dimensions and geometries such that the rectilinear third portion of the at least one bar is parallel to the closure panel.

11. An aircraft comprising:
a fuselage with a skin in which is made an opening, the skin delimiting the interior and the exterior of the fuselage,
a closure panel mobile between a closed position and an open position in which said closure panel uncovers the opening and
a support including a base fastened to the fuselage,
at least one bar and an articulation between said at least one bar and said base allowing the at least one bar to occupy a position retracted inside the fuselage and a position deployed outside the fuselage,
wherein the articulation is a pivoting connection,
wherein the support includes a locking system configured to occupy a locked state in which it immobilizes the at least one bar in rotation and an unlocked state in which it allows the rotation of the at least one bar,
wherein the at least one bar includes a head connected to the base by the pivot, said head including at least one notch for the deployed position and wherein the locking system includes a lever with a projecting shape that cooperates with the notch of the head when the at least one bar is in the deployed position, said lever being mobile between a position away from the head of the at least one bar that corresponds to the unlocked state and a position in contact with the head of the at least one bar.

12. An aircraft comprising:
a fuselage with a skin in which is made an opening, the skin delimiting the interior and the exterior of the fuselage,
a closure panel mobile between a closed position and an open position in which said closure panel uncovers the opening and
a support including a base fastened to the fuselage,
at least one bar and an articulation between said at least one bar and said base allowing the at least one bar to occupy a position retracted inside the fuselage and a position deployed outside the fuselage,
wherein the articulation is a pivoting connection,
wherein the pivot axis of the at least one bar is between an exterior surface and an interior surface of the fuselage,
wherein the at least one bar comprises:
a head connected to the base by the pivot,
a rectilinear first portion,
a cranked second portion and
a rectilinear third portion,
the rectilinear first portion and the cranked second portion of the at least one bar having dimensions and geometries such that the rectilinear third portion of the at least one bar is parallel to the closure panel.

Assignees

• Airbus Operations Sas
• Airbus Operations Sas

Inventors

• Salgues Patrick
• Neveu Anne-Laure

Classifications

• B64C1/1461 Primary

  Structures of doors or surrounding frames · CPC title

• B64C1/1407 Primary

  Doors; surrounding frames · CPC title