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公开(公告)号：US20180149113A1
公开(公告)日：2018-05-31
申请号：US15823053
申请日：2017-11-27
Applicant: Airbus Operations (S.A.S.) , Airbus (S.A.S.)
Inventor： Thierry Surply , Alain Porte , Patrick Oberle , Eric Haramburu , Thomas Sauvalle , Benoit Letay , Frédéric Piard , Vincent Billerot , Franck Oundjian
CPC classification number: F02K1/70 , F01D25/24 , F02K1/72 , F02K1/763 , F05D2220/323 , F05D2250/42
Abstract: A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.
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公开(公告)号：US20180032482A1
公开(公告)日：2018-02-01
申请号：US15658170
申请日：2017-07-24
Applicant: AIRBUS (S.A.S.)
Inventor： Jaouad BERRAJAA , Joel DUFOUR
CPC classification number: G06F17/212 , G06F11/1487 , G06F11/1492 , G06F11/1666 , G06F11/167 , G06F11/32 , G06F17/2205 , G06T11/60
Abstract: A device for displaying a document includes a display screen, a human-machine interface, a first memory zone and at least one second memory zone separate from the first memory zone. The zones are configured to contain similar information. A processor is configured to execute a first process and at least one second process when a display request is received via the human-machine interface. Those processes include respectively reading first information in the first memory zone and second information in the second memory zone. That information corresponds to the display request. The processes also include respectively producing a first display layer and a second display layer associated with the display screen, the first display layer and the second display layer being displayed on the display screen superimposed.
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93.发明申请公开(公告)号：US20170341774A1
公开(公告)日：2017-11-30
申请号：US15601473
申请日：2017-05-22
Applicant: AIRBUS (S.A.S.)
Inventor： Mei DING
Abstract: The present disclosure relates to a structural component of an aircraft wing body and an aircraft including the structural component. According to an aspect of the present disclosure, a structural component of an aircraft wing body is provided. The structural component includes a body part and a profile. The body part includes an edge portion formed by end portions of a first skin and a second skin of the body part superposed together. The profile is attached to the edge portion. The profile has an outer profile conforming to an outer profile of the body part such that the structural component, as a whole, exhibits an aerodynamic outer profile after the profile is attached to the edge portion. The profile is attached to the edge portion via a plurality of separate intermediate members or by contacting the edge portion.
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94.发明申请公开(公告)号：US20170337822A1
公开(公告)日：2017-11-23
申请号：US15594242
申请日：2017-05-12
Applicant: AIRBUS OPERATIONS (S.A.S.) , AIRBUS (S.A.S.)
Inventor： Andreas REINKE , Sebastian KAUERTZ
IPC: G08G5/00
CPC classification number: G08G5/0008 , B64D45/00 , G08G5/0013 , G08G5/0021 , G08G5/0091
Abstract: A method to identify the proximity of a wake turbulence and to generate a report relative to that proximity. A method implemented by an aircraft comprising a processor makes it possible to identify the proximity of a wake turbulence and to generate a report relative to that proximity. The method includes a data acquisition step during which the processor retrieves and records the data relative to each generating aircraft present around the aircraft. In a position estimation step, the processor estimates the position of the wake turbulences generated by each generating aircraft. In a proximity step, the processor determines if the aircraft is close to at least one of the wake turbulences. In a generation step, the processor generates a report containing the data relative to each wake turbulence. The method makes it possible to identify the proximity of a wake turbulence in the vicinity of the aircraft and to automatically record the data relative to that wake turbulence.
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公开(公告)号：US20170274977A1
公开(公告)日：2017-09-28
申请号：US15466743
申请日：2017-03-22
Applicant: AIRBUS (S.A.S.)
Inventor： Feng ZHANG , Li GUO
Abstract: The present disclosure relates to a sealing device and an associated flight control surface mechanism and an associated aircraft. According to an aspect of the present disclosure, a sealing device (100, 100′) for a flight control surface mechanism (10) of an aircraft (1) is provided, the flight control surface mechanism includes a fixed part (20) and a movable wing surface (40), the movable wing surface is attached to the fixed part in a manner of being movable relative to the fixed part. The sealing device includes a fixed seal (120) attached to the fixed part and a movable seal (140, 140′) attached to the movable wing surface so as to move with the movement of the movable wing surface, the movable seal and the fixed seal cooperate with each other in order to provide an aerodynamic sealing for the flight control surface mechanism.
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Patent Agency Ranking
公开(公告)号：US09737937B2
公开(公告)日：2017-08-22
申请号：US14471370
申请日：2014-08-28
Applicant: Airbus (S.A.S.)
Inventor： Mickaël Matignon
IPC: B23Q35/10 , B23B39/26 , B23B39/14 , B23B45/00 , B23B47/28 , B23B49/02 , B24B17/02 , B23Q1/54 , B23Q3/04 , B44B3/00
CPC classification number: B23B39/14 , B23B39/26 , B23B45/003 , B23B47/28 , B23B49/02 , B23B2270/34 , B23Q1/5462 , B23Q3/04 , B23Q35/10 , B23Q2735/004 , B23Q2735/045 , B24B17/021 , B44B3/002 , Y10T408/567 , Y10T409/301232 , Y10T409/301456 , Y10T409/30252
Abstract: A tool support is disclosed including-a fixed part, a moving part that is movable relative to the fixed part, a first crossmember linked to the moving part and a second crossmember. A tool includes a tool axis linked to the first and second crossmembers by pivoting links including articulation axes. A pointer is provided with a pointer axis parallel to the tool axis, the pointer being linked to the first and second crossmembers by pivoting links including articulation axes, with the articulation axes being parallel to one another. The tool support includes an immobilizer of occupy a first immobilized state in which it prevents a rotational movement on at least one articulation axis and a second released state in which it allows rotational movement on the articulation axes.
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公开(公告)号：US09676567B2
公开(公告)日：2017-06-13
申请号：US14303935
申请日：2014-06-13
Applicant: Airbus Operations GmbH , Airbus S.A.S.
Inventor： Uwe Panzram , Joerg Klockgether , Philippe Le Bigot , Peter Esteie , Netra Gowda
CPC classification number: B65G51/03 , B64C1/20 , B64D9/00 , B65D88/127 , B65D88/14 , B65D88/546 , B65D2590/0083
Abstract: A cargo compartment configured to be installed in an aircraft and to accommodate a plurality of cargo receiving devices is provided. The cargo compartment surrounds a compartment interior space, and includes a floor structure arrangement having a floor surface facing the compartment interior space and configured to support cargo receiving devices loaded into the cargo compartment. The cargo compartment includes two opposite side walls extending laterally of the floor structure arrangement away from the floor surface, and the side walls include an entrance opening for access to the compartment interior space. The floor structure arrangement also includes an air cushion device having a plurality of cushion nozzles distributed in the floor surface, and the cushion nozzles are configured to blow air up from the floor surface in a direction perpendicular to the floor surface.
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公开(公告)号：US20170103590A1
公开(公告)日：2017-04-13
申请号：US14880754
申请日：2015-10-12
Applicant: AIRBUS (S.A.S.) , AIRBUS OPERATIONS LIMITED
Inventor： Dominique GAREL , Jean-Max HUET , Tim CHANT , Simon WESELBY , Anne-Lise RICARD
Abstract: An aerodynamic audit system is provided for performing an audit process of an aircraft using a computing device via a network. An inspection module inspects at least a portion of the aircraft for locating and measuring any aerodynamic defects present by generating an inspection list having a predetermined inspection path. A display device displays the inspection path and accepts a measurement of any located aerodynamic defect. A fuel penalty estimation module calculates an estimated fuel penalty of the aerodynamic defect based on the measurement of the corresponding aerodynamic defect. A defect correction analysis module analyzes the aerodynamic defect based on a cost and benefit assessment. A findings collection module generates an audit report based on the inspection and analysis of the aerodynamic defect. A database stores data associated with the aerodynamic defect and the corresponding fuel penalty based on the cost and benefit assessment.
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公开(公告)号：US09600944B1
公开(公告)日：2017-03-21
申请号：US14880754
申请日：2015-10-12
Applicant: AIRBUS (S.A.S.) , AIRBUS OPERATIONS LIMITED
Inventor： Dominique Garel , Jean-Max Huet , Tim Chant , Simon Weselby , Anne-Lise Ricard
Abstract: An aerodynamic audit system is provided for performing an audit process of an aircraft using a computing device via a network. An inspection module inspects at least a portion of the aircraft for locating and measuring any aerodynamic defects present by generating an inspection list having a predetermined inspection path. A display device displays the inspection path and accepts a measurement of any located aerodynamic defect. A fuel penalty estimation module calculates an estimated fuel penalty of the aerodynamic defect based on the measurement of the corresponding aerodynamic defect. A defect correction analysis module analyzes the aerodynamic defect based on a cost and benefit assessment. A findings collection module generates an audit report based on the inspection and analysis of the aerodynamic defect. A database stores data associated with the aerodynamic defect and the corresponding fuel penalty based on the cost and benefit assessment.
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公开(公告)号：US09580163B2
公开(公告)日：2017-02-28
申请号：US14529404
申请日：2014-10-31
Applicant: AIRBUS S.A.S.
CPC classification number: B64C1/069 , B64C9/02 , F16C11/02 , F16C2326/43
Abstract: The present invention relates to a bending-sustaining joint and an aircraft including the same. The bending-sustaining joint includes a body for attaching to a support structure, the body having a first end with a first bore including an internal thread portion and a non-threaded portion; a sleeve including a fitting portion which can be fit into the non-threaded portion of the first bore, a bearing portion for bearing a born member and a through hole; and a bolt member including a thread section and a bolt head which can abut an end face of the sleeve, the thread section of the bolt member being capable of passing through the through hole of the sleeve and being screwed into the internal thread portion of the first bore so as to secure the sleeve to the body.
Abstract translation: 本发明涉及一种弯曲维持接头和包括该弯曲维持接头的飞行器。 所述弯曲维持接头包括用于附接到支撑结构的本体，所述本体具有第一端，所述第一端具有包括内螺纹部分和非螺纹部分的第一孔; 套筒，其包括可以装配到第一孔的非螺纹部分中的装配部分，用于承载出生构件的轴承部分和通孔; 以及螺栓构件，其包括螺纹部和螺栓头，所述螺栓部能够抵接所述套筒的端面，所述螺栓构件的螺纹部能够穿过所述套筒的通孔并被螺纹连接到所述套筒的内螺纹部分中 第一孔，以便将套筒固定到身体上。
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