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1. 发明公开

EP4389592A1 AN AIRCRAFT DOOR WITH AN ADJUSTMENT SYSTEM FOR ADJUSTING THE POSITION OF THE DOOR LEAF RELATIVE TO THE DOOR FRAME 审中-实审
公开(公告)号：EP4389592A1
公开(公告)日：2024-06-26
申请号：EP22214699.5
申请日：2022-12-19
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： BECKER, Stefan , TENDYRA, Thomas , MERKEL, Christoph , FERBER, Christian
IPC分类号： B64C1/14
CPC分类号： B64C1/143
摘要： The present technology relates to an aircraft door 200. The aircraft door 200 includes a door leaf 210, a door frame 610, a support arm assembly 220, and first and second connecting elements 380, 680. The first connecting element 380 connects the support arm assembly 220 with the door leaf 210 and includes a first adjustment unit 300 that is adapted for adjusting the position of the door leaf 210 relative to the door frame 610 along a first axis (x-axis). The second connecting element 680 connects the support arm assembly 220 with the door frame and includes a second adjustment unit 600 that is adapted for adjusting the position of the door leaf 210 relative to the door frame 610 along a second axis (z-axis) that is perpendicular to the first axis (x-axis).

2. 发明公开

EP3168138A1 AIRCRAFT DOOR ASSEMBLY 失效
标题翻译：飞机门组件
公开(公告)号：EP3168138A1
公开(公告)日：2017-05-17
申请号：EP15193810.7
申请日：2015-11-10
申请人： Airbus Operations GmbH
发明人： ERBEN, Johann Konrad
IPC分类号： B64C1/14
CPC分类号： B64C1/1461 , B64C1/1407 , B64C1/143 , E05B15/0086 , E05B17/2007 , E05B17/2034 , E05B79/10 , E05B83/42 , E05C3/02 , E05C3/12 , E05C9/00 , E05C19/12
摘要： A door assembly, particularly for doors of passenger aircraft, includes a door frame, a door having a door body hingedly installed in the door frame, at least one hooking pintle (4) attached to the door frame or an edge of the door body extending along a pintle axis, and at least one door latch (2) connected to an edge of the door body or the door frame, respectively, the door latch having a substantially C-shaped latch body (2a) configured to rotate around an axis parallel to the pintle axis of the hooking pintle (4). The door assembly further includes a bistable latch and hook mechanism configured to catch the door latch (2) in hooking engagement with the hooking pintle (4) and to retain the door latch (2) in a direction perpendicular to the door body in an overcenter position.
摘要翻译：一种门组件，特别是用于客机门的门组件，包括门框，具有铰接地安装在门框中的门体的门，附接到门框或门体的边缘的至少一个钩销（4）（2），所述门闩（2）分别连接到所述门体或所述门框的边缘，所述门闩具有大致C形的闩锁主体（2a），所述闩锁主体构造成围绕平行的轴线到钩销（4）的枢轴线。所述门组件还包括双稳态闩锁和钩机构，所述双稳态闩锁和钩机构构造成在与所述钩销（4）钩接合的情况下钩住所述门闩（2）并且在垂直于所述门体的方向上将所述门闩（2）保持在偏心位置。

3. 发明公开

EP2842873A1 Short term, autonomous, electrical power supply system 失效
标题翻译： Kurzfristiges，自主权Stromversorgungssystem
公开(公告)号：EP2842873A1
公开(公告)日：2015-03-04
申请号：EP13400018.1
申请日：2013-08-30
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Hübner, Christoph , Renner, Uwe
IPC分类号： B64D41/00 , B64C1/14
CPC分类号： B64D25/08 , B64C1/1407 , B64C1/143 , E05F11/54 , E05F15/603 , F01D15/10 , F02C3/20 , F42B3/006 , F42B3/04 , H02K7/1823
摘要： The invention relates to a short term, autonomous, electrical power supply system, particularly an emergency short term, autonomous, electrical power supply system. Said system comprises an actuator with an electrical motor (14), an electrical generator (15) for driving said electrical motor (14) of said actuator, a turbine (13) in driving engagement with said electrical generator (15), an generator (7) of combustible, fluidic energy, a fluid line (10) from said generator (7) to said turbine (13), a control unit (5), and an igniter (9) arranged inside said generator (7) and controlled by said control unit (5).
摘要翻译：本发明涉及一种短期的，自主的电力供应系统，特别是紧急短期的自主电力供电系统。所述系统包括具有电动机（14）的致动器，用于驱动所述致动器的所述电动机（14）的发电机（15），与所述发电机（15）驱动接合的涡轮机（13），发电机 7）可燃的流体能量，从所述发电机（7）到所述涡轮机（13）的流体管线（10），控制单元（5）和布置在所述发电机（7）内的点火器（9），并由所述控制单元（5）。

4. 发明公开

EP2374713A2 Türrahmenanordnung und Tür, insbesondere für Luft- oder Raumfahrzeuge 审中-公开
标题翻译：门框和门组件，特别是用于飞机或航天器
公开(公告)号：EP2374713A2
公开(公告)日：2011-10-12
申请号：EP11161292.5
申请日：2011-04-06
申请人： Deutsches Zentrum für Luft- und Raumfahrt e.V.
发明人： Kolesnikov, Boris , Ströhlein, Tobias , Assing, Heiko , Hühne, Christian , Fink, Axel , Niemann, Steffen
IPC分类号： B64C1/14
CPC分类号： B64C1/1461 , B64C1/143
摘要： Eine Türrahmenanordnung für einen Rumpf, insbesondere eines Luft- oder Raumfahrzeugs besitzt einen Türausschnitt (20) in dem Rumpf (10). Der Bereich (11) des Rumpfes (10) um den Türausschnitt (20) ist in Semimonocoque-Bauweise mit einer Haut (12), Stringern (13) und Spanten (14) aufgebaut. Der Türausschnitt (20) wird von einer verschließbaren Tür (30) ausgefüllt, welche in Semimonocoque-Bauweise mit einer Haut (32), Querversteifungselementen (33) und Längsversteifungselementen (34) aufgebaut ist. Außerdem ist vorgesehen, dass in dem Bereich (11) des Rumpfes (10) um den Türausschnitt (20) benachbart zu zumindest einer Ecke (21, 22, 23, 24) des Türausschnitts (20) mindestens ein zusätzliches Versteifungselement (41, 42, 43, 44) angeordnet ist, welches mit den Stringern (13) und Spanten (14) des Flugzeugrumpfes (10) in diesem Bereich (11) ein lokales Fachwerksystem (51) bildet, und dass in der Tür (30) mindestens ein zusätzliches Versteifungselement (46, 48) angeordnet ist, welches bei verschlossener Tür (30) mit den Stringern (13) und Spanten (14) des Bereiches (11) des Flugzeugrumpfes (10) um den Türausschnitt (20) ein lokales Fachwerksystem (53) bildet, und dass das zusätzliche Versteifungselement (46, 48) an der Verbindungslinie zwischen der Tür (30) und dem Bereich (11) des Flugzeugrumpfes (10) um den Türausschnitt (20) kraftschlüssige, lösbare Verbindungen (57, 58) aufweist.
摘要翻译：用于身体的门架组件，尤其是飞机或航天器具有在船体（10）的门开口（20）。船体（10）围绕门开口（20）的区域（11）在半单体结构与皮肤（12）纵梁（13）和肋（14）构成。门切口（20）由在半单体结构与皮肤（32），横向加强元件（33）和纵向加强构件（34）构成的上锁的门（30）填充。另外，在船体（10）围绕门开口（20）的区域（11）被设置成邻近至少所述门开口的角（21，22，23，24）（20）的至少一个附加的加强元件（41，42， 43，44）被布置形成（与所述机身（10）的桁条13）和肋（14）在这个区域（11）的本地桁架系统（51），并且（在门30）的至少一个附加的加强元件（46，48）被布置成，其与所述机身（10）围绕门开口（20）的本地桁架系统（53）的区域（11）的一个封闭的门（30）连接到桁条（13）和肋（14）形成，且具有在所述门（30）和所述机身（10）围绕门开口（20）压入配合，可拆卸的连接（57，58）的区域（11）之间的连接线的附加加强元件（46，48）。

5. 发明公开

EP2236411A1 Locking device for an aircraft door 审中-公开
标题翻译： VerriegelungsvorrichtungfüreineFlugzeugtür
公开(公告)号：EP2236411A1
公开(公告)日：2010-10-06
申请号：EP09400010.6
申请日：2009-03-30
申请人： Eurocopter Deutschland GmbH
发明人： Trott, Dirk
IPC分类号： B64C1/14
CPC分类号： B64C1/143
摘要： The invention relates to a locking device for a rectangular aircraft door (1) that is coupled to an aircraft fuselage (3) by way of swinging means, to which fuselage (3) in the region of both opposing fuselage frame elements (4a, 4b) In each case at least two guide links (5a, 5b; 5a', 5b'), spaced apart from each other, for keeping the aircraft door (1) closed in a lowered closed position are provided, which guide links (5a, 5b; 5a', 5b') interact with associated guide rollers (7a, 7b; 7a', 7b') that are arranged on the aircraft door (1), wherein the guide track of said guide rollers (7a, 7b; 7a', 7b'), starting from a groove opening (10), first extends in a horizontal track section (11) in the closing direction of the aircraft door (1) and after moving through a subsequent deflection radius (12) extends to a vertical track section (13) until the lowered closed position of the aircraft door (1) at the end of the vertical track section (13) has been reached, wherein the vertical track section (13) after the deflection radius (12) makes a transition to an inwards section (8) that is partly directed in the direction of opening of the aircraft door (1), with an inwards angle (α) exceeding 6° relative to the door area (9) that is subjected to pressure, in order to hold the aircraft door (1) securely closed as a result of the existing interior pressure in the cabin.
摘要翻译：本发明涉及一种用于矩形飞机门（1）的锁定装置，其通过摆动装置联接到飞行器机身（3），机身（3）在相对的机身框架元件（4a，4b）的区域中在每种情况下，提供了彼此间隔开的用于将飞行器门（1）关闭在降低的关闭位置的至少两个导向连杆（5a，5b; 5a'，5b'），所述导向连杆（5a， 5b; 5a'，5b'）与布置在飞行器门（1）上的相关联的导辊（7a，7b; 7a'，7b'）相互作用，其中所述导辊（7a，7b; 7a'）的导轨，7b'）从凹槽开口（10）开始，首先在飞行器门（1）的关闭方向上的水平轨道部分（11）中延伸，并且在移动通过随后的偏转半径（12）之后延伸到垂直轨道部分（13）直到达到垂直轨道部分（13）的端部处的飞行器门（1）的下降的关闭位置，其中垂直轨道在偏转半径（12）之后，向内侧部分（8）向内侧部分（8）转动，该部分朝向飞行器门（1）的打开方向部分地指向，相对于飞行器门（1）的向内角度（±）超过6° 受到压力的门区域（9）为了保持飞行器门（1）由于机舱内现有的内部压力而牢固地关闭。

6. 发明公开

EP1569845A1 LUFTFAHRZEUG-TÜRANORDNUNG 有权转让
标题翻译：飞机舱门安排
公开(公告)号：EP1569845A1
公开(公告)日：2005-09-07
申请号：EP03780124.8
申请日：2003-12-05
申请人： EUROCOPTER DEUTSCHLAND GmbH
发明人： WIERS, Andreas , SUCHY, Rainer , KUNZE, Steffen , STERR, Matthias
IPC分类号： B64C1/14
CPC分类号： B64C1/143 , B64C1/1407
摘要： The invention relates to an aircraft door arrangement, especially for an aeroplane, said arrangement comprising a door, a doorframe, a supporting section with a pivotal axis (AD) on the door side, along which the door is pivotably positioned, and a pivotal axis (AF) on the frame side, along which the supporting section (8) is pivotably positioned on the door frame. At least the pivotal axis (AD) on the door side is defined by two articulations (G1, G2) which are interspaced in the vertical direction (Y) of the supporting section (8), at least one (G1; G2) of said articulations comprising two vertically (Y) interspaced bearings (L1a, L1b). The inventive door arrangement also comprises a pivotal drive (10) which is arranged on the door side of the supporting section (8) and is used to pivot the door, and an output element (12; 14, 16) which is coupled to the pivotal drive (10) and the door and transfers an actuating movement of the pivotal drive (10) to the door. Said aircraft door arrangement is characterised in that one (L1b) of the two bearings (L1a, L1b) of at least one (G1) of the articulations (G1, G2) on the frame side is embodied (L1B) as a pivotal drive mounting (34) to which the pivotal drive (10) is fixed.

7. 发明公开

EP0677438A1 Türsystem, insbesondere für ein Passagierflugzeug 失效
标题翻译： Türsystem，insbesonderefürein Passagierflugzeug。
公开(公告)号：EP0677438A1
公开(公告)日：1995-10-18
申请号：EP95103923.9
申请日：1995-03-17
申请人： EUROCOPTER DEUTSCHLAND GmbH
发明人： Erben, Hannes , Buchs, Wolfgang
IPC分类号： B64C1/14
CPC分类号： B64C1/143 , B64C1/1407
摘要： Vorgestellt wird ein Türsystem, insbesondere für ein Passagierflugzeug, mit einer zwischen Türblatt (2) und Türrahmen (12) wirkenden Trag- und Führungseinrichtung (10, 14) und einer zwischen dieser und dem Türblatt angeordneten Hubeinrichtung (18, 20, 22), die das Türblatt am Ende der Schließbewegung quer zur Bewegungsbahn (B) der Führungseinrichtung unter formschlüssigem Eingriff mit türrahmenfesten Aufnahmeelementen (4) in die vollständige Schließlage verfährt und zu Beginn des Öffnungsvorganges mit entgegengesetzter Hubrichtung (A) aus dem formschlüssigen Eingriff herausbewegt, wobei die Hubeinrichtung eine Hubkinematik (18, 20) zur Steuerung der Türblatt-Hubbewegung und einen zugeordneten Hubantrieb (22) enthält.
Um bei einem derartigen Türsystem einen hohen Sicherheitsstandard und zugleich eine einfache gewichtsparende Bauweise zu gewährleisten, ist das Türblatt mit einer elektrischen Antriebseinheit (22) für den Hubantrieb und einer parallel zur elektrischen Ansteuerung des Hubantriebs mechanisch durch einen Türöffnungsbefehl freischaltbaren, die Hubeinrichtung in der vollständigen Schließlage selbsttätig türblattfest verriegelnden Hubsicherung (28) versehen.
摘要翻译：门具有一个带有用于提升电动驱动单元（22）的面板（2）。平行于提升单元的电气控制是紧固件（28），其通过机械开门指令自动地锁定门板并释放。门提升机构由位于门板上的支撑件和导向件（10,14）之间的四杆连接件（18,20）组成。电动线性致动器（22）在四杆连杆的对角线上操作。具有压缩空气蓄能器（58）的气动应急驱动机构（54）通过同时释放提升紧固件来启动。

8. 发明公开

EP0518429A1 Aircraft door handle assembly 失效
标题翻译： Türgriffaggregateines Flugzeuges。
公开(公告)号：EP0518429A1
公开(公告)日：1992-12-16
申请号：EP92201647.2
申请日：1992-06-05
申请人： THE BOEING COMPANY
发明人： Noble, Donald Richard , Poechlauer, Kurt , Ulman, Richard James
IPC分类号： B64C1/14 , E05B5/00
CPC分类号： B64C1/143 , B64C1/1407 , E05B5/003 , Y10S292/31 , Y10T70/5761 , Y10T292/57 , Y10T292/82
摘要： A handle assembly (12) for controlling an aircraft door (14) latch mechanism so that the door can be opened or closed from either inside or outside the aircraft. The assembly includes an inner shaft (58) that is connected to the latch mechanism (26) so as to control the opening and closing of the door (14), and an outer shaft (56) that overlaps the inner shaft (58) and that can be telescopically extended away from inner shaft. An inside handle (28) is attached to the inner shaft (58) so as to rotate the shaft. Rotation of the outer shaft (56) is controlled by an outside handle (52) attached thereto. An inner clutch half (130) is attached, by splines, to the inboard end of the outer shaft. An outer clutch half (132) is attached, by splines, to the outboard end of the inner shaft. The clutch halves are normally spaced away from each other. When the outside handle (52) and the outer shaft (56) are extended, the clutch halves interlock so that the shafts will rotate in unison. An actuator disarming assembly (60) with a translating pivoting crank (286) is attached to the outer shaft (56). When the outside handle (52) and the outer shaft (56) are extended, the crank (286) pivots to cause the disarming mechanism to disarm any actuator that may be attached to the door (14). This prevents inadvertent triggering of the actuator when persons outside the aircraft are trying to open the door.
摘要翻译：一种用于控制飞行器门（14）闩锁机构的手柄组件（12），使得门能够从飞行器的内部或外部打开或关闭。组件包括连接到闩锁机构（26）以控制门（14）的打开和关闭的内轴（58）和与内轴（58）重叠的外轴（56）和可以远离内轴伸缩。内侧手柄（28）安装在内轴（58）上以使轴旋转。外轴（56）的旋转由附接到其上的外手柄（52）控制。内离合器半部（130）通过花键连接到外轴的内侧端部。外离合器半部（132）通过花键连接到内轴的外侧。离合器半部通常彼此间隔开。当外手柄（52）和外轴（56）延伸时，离合器半部互锁，使得轴将一致地旋转。具有平移枢转曲柄（286）的致动器解除组件（60）附接到外轴（56）。当外手柄（52）和外轴（56）伸出时，曲柄（286）枢转以使解除装置解除任何可附接到门（14）的致动器。这可以防止飞机外的人员试图打开门时意外触发执行器。

9. 发明公开

EP0317037A3 Hinge mechanism for aircraft door 失效
标题翻译：飞机门铰链机构
公开(公告)号：EP0317037A3
公开(公告)日：1990-05-16
申请号：EP88202607.3
申请日：1988-11-21
申请人： THE BOEING COMPANY
发明人： Maraghe, Alex , Puncoch, Miloslav
IPC分类号： B64C1/14 , E05D3/06
CPC分类号： B64C1/143 , B64C1/1407 , E05D3/12 , E05D3/18 , E05Y2900/502 , E05Y2900/531 , Y10T16/5445 , Y10T16/5474 , Y10T16/5476
摘要： A passenger door (34) is connected to an aircraft fuselage (12) by a hinge mechanism (10) having an elongated goose-neck hinge member (22). One end of the hinge-member is pivotally connected to an idler crank arm (18) that is pivotally connected to the fuselage. The other end of the goose-neck member is pivotally connected to the door (34). A guide arm (36) connected to the door and carried by the idler crank arm (18) controls door movement. An end of the guide arm (36) has a pin (48) that follows a groove in an "S"-shaped guide track (44). The shape of the track (44) causes the guide arm to initially pivot and translate the door partially inwardly into the fuselage during opening movement, and then swing the door outwardly until it is parallel with the fuselage's outer surface.

10. 发明授权

EP0192503B1 Mécanisme pour l'actionnement automatique d'un dispositif de sauvetage lors de l'ouverture d'une porte d'issue 失效转让
标题翻译：退出门自动启动救援装置的机构已开启
公开(公告)号：EP0192503B1
公开(公告)日：1988-05-11
申请号：EP86400077.3
申请日：1986-01-15
申请人： AEROSPATIALE Société Nationale Industrielle
发明人： Bokalot, Jean
IPC分类号： B64D25/14
CPC分类号： B64C1/143 , B64C1/1407 , B64D25/14 , Y10S244/905

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