公开(公告)号：US20170113784A1

公开(公告)日：2017-04-27

申请号：US15332247

申请日：2016-10-24

Applicant: AIRBUS OPERATIONS (SAS)

Inventor： Bernard GUERING ,  Laurent SAINT-MARC

IPC: B64C13/04 ,  B64C13/30

Abstract: A suspended rudder bar for aircraft and aircraft having a suspended rudder bar, which includes a set of primary hinges, a set of secondary hinges including control and synchronization devices, and a set of linkages generating functional and structural links between the set of primary hinges and the set of secondary hinges, wherein the primary hinges are configured to be suspended at least on a structure supporting the instrument panel of the flight deck of the aircraft, and the secondary hinges configured to be suspended at least on a structural component of an area situated forward of the flight deck.

公开(公告)号：US20190185165A1

公开(公告)日：2019-06-20

申请号：US16224071

申请日：2018-12-18

Applicant: Airbus Operations SAS

Inventor： Bernard GUERING ,  Laurent SAINT-MARC

IPC: B64D11/06 ,  B64D25/08

CPC classification number: B64D11/0629 ,  B60N2/00 ,  B64D11/06 ,  B64D11/0627 ,  B64D11/0689 ,  B64D25/04 ,  B64D25/08

Abstract: A pilot's seat offering an evacuation device. The seat comprises a ladder fixed to the rear of the back and covered by a detachable cover associated with the seat and deployable between a storage position retracted inside the cover and a deployed evacuation position, in which case the cover is detached. Thus, the evacuation device is incorporated harmoniously into the seat which offers a solid base for the evacuation ladder.

公开(公告)号：US20180178894A1

公开(公告)日：2018-06-28

申请号：US15847090

申请日：2017-12-19

Applicant: Airbus Operations SAS

Inventor： Bernard Guering ,  Laurent SAINT-MARC

IPC: B64C1/06 ,  B64F5/10

CPC classification number: B64C1/066 ,  B64C1/063 ,  B64C1/068 ,  B64C1/40 ,  B64D2011/0046 ,  B64F5/10

Abstract: A bendable element is formed at least from an inflatable envelope, a first bendable, elongate base plate attached to a first face of the inflatable envelope, a second bendable, elongate base plate, attached to a second face of the inflatable envelope and shorter than the first base plate, and links connecting the first base plate to the second base plate. The links are slack when the inflatable envelope is in a deflated state. The action of inflating the inflatable envelope causes the first and second base plates to bend in a direction of curvature extending from the first base plate to the second base plate, by means of the tensioning of the links such that the links extend along radii of curvature common to the first and second base plates while keeping the second base plate centered longitudinally relative to the first base plate.

公开(公告)号：US20180281934A1

公开(公告)日：2018-10-04

申请号：US15939869

申请日：2018-03-29

Applicant: Airbus Operations SAS

Inventor： Bernard GUERING ,  Laurent SAINT-MARC

IPC: B64C25/12 ,  B64C25/34 ,  B64C39/10

Abstract: A front landing gear comprising an undercarriage and a landing gear bay, the undercarriage including a single wheel, a landing gear strut and a stay rod, the undercarriage being movable between a retracted position in which it is stowed inside the landing gear bay and a deployed position in which it extends mainly outside the landing gear bay and the aircraft, the wheel then extending in a median longitudinal plane of the aircraft. The landing gear strut is laterally offset, extending in a plane strictly parallel to the plane of the wheel. The landing gear strut is articulated about a longitudinal axis pivot connection such that, when the undercarriage is moved between its retracted and deployed positions, the landing gear strut moves in a transverse plane. The front landing gear is particularly suitable for an aircraft of flying wing type.

公开(公告)号：US20190047711A1

公开(公告)日：2019-02-14

申请号：US16057085

申请日：2018-08-07

Applicant: Airbus Operations SAS

Inventor： Bernard GUERING ,  Laurent SAINT-MARC

IPC: B64D13/08 ,  B64D13/06

Abstract: An aircraft comprising an air conditioning device positioned at least in part in the nosecone of the aircraft. This novel integration architecture makes it possible to reduce the volume of the belly pan of the aircraft and improve the aerodynamic performance thereof.

公开(公告)号：US20180305028A1

公开(公告)日：2018-10-25

申请号：US15959899

申请日：2018-04-23

Applicant: Airbus Operations SAS

Inventor： Bernard Guering ,  Laurent SAINT-MARC

IPC: B64D13/06

CPC classification number: B64D13/06 ,  B64C7/00 ,  B64D2013/0618 ,  B64D2231/02 ,  B64F1/362

Abstract: An air intake system for an aircraft having a ventral fairing and comprising a scoop having a ventral wall with a first coupling and an opening. The scoop is movable between a flush position in which the ventral wall is flush with the ventral fairing and a catchment position in which the opening is beneath the ventral fairing, and the ventral wall is pierced by a through hole designed to be connected to a flexible pipe of an air conditioning unit. A hatch is movably mounted on the scoop between an open position not blocking the opening and a closed position blocking the opening, the open position can be attained only when the scoop is in the catchment position. A return element forces the hatch into the closed position, and a plug has a second coupling which cooperates with the first coupling to removably secure the plug.