公开(公告)号：US12116105B2

公开(公告)日：2024-10-15

申请号：US17505093

申请日：2021-10-19

申请人： AMSAFE BRIDPORT LIMITED

发明人： James Barry Homewood

IPC分类号： B64C1/10 ,  A62C3/08 ,  B64C1/00 ,  B64C1/14

CPC分类号： B64C1/10 ,  A62C3/08 ,  B64C1/00 ,  B64C1/1469 ,  B64C2001/009

摘要： A fabric barrier for an aircraft compartmental barrier includes a fabric barrier portion and a flexible crosspiece, wherein at least part of one edge of the fabric barrier portion terminates at the flexible crosspiece, wherein the flexible crosspiece is adapted to fit into and be retained within a partially covered groove, wherein the partially covered groove includes a pair of opposing flange portions covering a groove whereby a central longitudinal portion of the groove remains uncovered, wherein the flexible crosspiece is adapted to be released from the partially covered groove by passing between the pair of opposing flange portions during a decompression event. A decompression system for an aircraft compartmental barrier includes said fabric barrier, and a method for isolating two internal volumes within an aircraft using said decompression system.

公开(公告)号：US12110732B2

公开(公告)日：2024-10-08

申请号：US17862106

申请日：2022-07-11

申请人： Adams Rite Aerospace Inc.

发明人： Morteza Yadollahi ,  Alan Manara

IPC分类号： F16F7/12 ,  B64C1/14 ,  E05B77/54 ,  E05B81/56 ,  E05F3/04 ,  E05F5/06 ,  E05F5/10 ,  F16F9/00 ,  F16F9/19 ,  F16F9/48 ,  B64C1/00 ,  F16F9/16 ,  F16F9/30

CPC分类号： E05F5/06 ,  B64C1/1469 ,  E05B77/54 ,  E05B81/56 ,  E05F3/04 ,  E05F5/10 ,  F16F7/121 ,  F16F7/125 ,  F16F9/003 ,  F16F9/19 ,  F16F9/48 ,  B64C2001/009 ,  E05Y2201/212 ,  E05Y2900/502 ,  E05Y2900/531 ,  F16F9/165 ,  F16F9/303 ,  F16F2228/066 ,  F16F2236/04

摘要： A shock absorber includes a first end configured to be mechanically fastened to a first component, a second end configured to be mechanically fastened to a second component, a main body, a main shaft, and a primary piston. The primary piston configured to move within the main body and further configured to provide a first damping force by movement of a fluid through the primary piston while the main shaft moves a first distance. The shock absorber also includes a deformable solid material arranged in the main body. The primary piston configured to further move within the main body and further configured to provide a second damping force by deforming the deformable solid material after the main shaft moves the first distance.

公开(公告)号：US20170210460A1

公开(公告)日：2017-07-27

申请号：US15002723

申请日：2016-01-21

申请人： Gulfstream Aerospace Corporation

发明人： Todd Schartner ,  Clint Rupp

IPC分类号： B64C1/14

CPC分类号： B64C1/1461 ,  B64C1/1423 ,  B64C1/1469

摘要： The disclosed embodiments relate to an aircraft having an interior cabin door with a retractable header. Accordingly to non-limiting embodiments, an interior cabin door for an aircraft includes a door panel having an opening in a top portion thereof. A retractable header configured to retract into the opening in the door panel as the door panel moves toward an open position. As the door panel moves toward a closed position, a lifting system is configured to raise the retractable header to interface with the ceiling of the aircraft. The lifting system includes a four-bar mechanism, a cable and pulley system and a biasing member configured to upwardly bias the retractable header.

公开(公告)号：US20170043857A1

公开(公告)日：2017-02-16

申请号：US15284795

申请日：2016-10-04

申请人： Airbus Operations GmbH

发明人： Christian Seibt

IPC分类号： B64C1/14 ,  B64D11/06 ,  B64D11/00 ,  B64D11/02 ,  B64D11/04

CPC分类号： B64C1/1407 ,  B64C1/1423 ,  B64C1/1469 ,  B64D11/003 ,  B64D11/02 ,  B64D11/04 ,  B64D11/0691

摘要： To be able to transmit higher forces when retaining movable components on board an aircraft, a retaining system includes a support structure with a first retaining area and a second retaining area having a movable locking element, and a movable component with a locking receptacle forming a locking device with the locking element, and a retaining device. The movable component is movably attached to the first retaining area with the retaining device, and the movable component can be locked on the second retaining area with the locking device. The at least one movable locking element can be moved between an open setting (SOFF) and a locked setting (SVER), wherein the at least one movable locking element engages with the locking receptacle in the locked setting, so that the movable component is temporarily immovably retained, and allows the movable component to move in the open setting.

摘要翻译： 为了能够在将飞行器上的可移动部件保持时能够传递更高的力，保持系统包括具有第一保持区域的支撑结构和具有可移动锁定元件的第二保持区域，以及具有形成锁定 具有锁定元件的装置和保持装置。 可移动部件通过保持装置可移动地附接到第一保持区域，并且可移动部件可以用锁定装置锁定在第二保持区域上。 所述至少一个可移动锁定元件可以在打开设置（SOFF）和锁定设置（SVER）之间移动，其中所述至少一个可移动锁定元件在所述锁定设置中与所述锁定插座接合，使得所述可移动元件暂时地 不可移动地保持，并且允许可移动部件在打开设置中移动。

公开(公告)号：US20160340019A1

公开(公告)日：2016-11-24

申请号：US14719420

申请日：2015-05-22

申请人： Gulfstream Aerospace Corporation

发明人： Robert J. Telmos

IPC分类号： B64C1/14 ,  B64C1/10

CPC分类号： B64C1/1461 ,  B64C1/10 ,  B64C1/1469 ,  B64C11/00 ,  B64D11/00

摘要： The disclosed embodiments relate to an aircraft having an interior door with a compressible header. Accordingly to non-limiting embodiments, a slideable door panel includes an opening in a top portion thereof to receive a compressible header configured to reside in the opening of the slideable door panel. The compressible header includes a biasing mechanism configured to upwardly bias the compressible header against the headliner when closed. The compressible header is also configured to allow lateral movement of the compressible header within the opening. The compressibility of the compressible header and lateral movement resist the formation of gaps between the compressible header and the headliner during flight.

摘要翻译： 所公开的实施例涉及具有带有可压缩头部的内部门的飞行器。 因此，在非限制性实施例中，可滑动门板包括在其顶部部分中的开口，以容纳构造成位于可滑动门板的开口中的可压缩集管。 可压缩的集管包括偏置机构，该偏置机构构造成当关闭时向上偏压可压缩的头部抵靠顶篷。 可压缩头部还被构造成允许可压缩头部在开口内的横向移动。 可压缩头部的压缩性和横向运动抵抗在可压缩头部和顶篷之间在飞行期间的间隙的形成。

公开(公告)号：US20160332718A1

公开(公告)日：2016-11-17

申请号：US15150674

申请日：2016-05-10

申请人： Airbus Operations S.A.S.

发明人： Bernard Guering

IPC分类号： B64C1/14 ,  E06B3/80 ,  B64D11/02 ,  E06B3/48

CPC分类号： B64C1/1438 ,  B64C1/1469 ,  B64D11/00 ,  B64D11/0023 ,  B64D11/02 ,  B64D45/0015 ,  B64D2011/0046 ,  E06B3/481 ,  E06B3/805

摘要： An access device enables controlled or secure communication between different areas of an enclosure, and in the example illustrated in the present application of an aircraft, while providing reduced size. The access device includes a folding door which, when in folded position, allows at least one of said openings to be closed and, when in deployed position, forms a security vestibule with at least one movable shutter allowing said opening created by the deployment of said folding door to be closed. By superimposing the main components of the security vestibule that said components allow to close, the device frees up the adjoining cabin space when the security vestibule is not in use.

摘要翻译： 接入设备能够在提供减小的尺寸的同时在外壳的不同区域之间以及飞行器的本申请中所示的示例中进行受控或安全的通信。 进入装置包括折叠门，折叠门在折叠位置时允许所述开口中的至少一个被关闭，并且当处于展开位置时，形成具有至少一个活动快门的安全前庭，允许所述开口由所述 折叠门关闭。 通过叠加所述部件允许关闭的安全前庭的主要部件，当安全前庭不使用时，该装置释放邻近的舱室空间。

公开(公告)号：US08136763B2

公开(公告)日：2012-03-20

申请号：US12520915

申请日：2007-12-21

申请人： Bruno Saint-Jalmes ,  Bernard Rumeau ,  Jason Zaneboni ,  Bruno Alquier ,  Jerome Javelle ,  Joachim Voelkner ,  Martin Geldien

发明人： Bruno Saint-Jalmes ,  Bernard Rumeau ,  Jason Zaneboni ,  Bruno Alquier ,  Jerome Javelle ,  Joachim Voelkner ,  Martin Geldien

IPC分类号： B64D11/00 ,  B64D11/06 ,  B64D13/00

CPC分类号： B64D11/02 ,  B64C1/1469 ,  B64D45/0015 ,  B64D2011/0046 ,  B64D2011/0076

摘要： A front portion of a fuselage of an aircraft including a cockpit, a washroom, an access corridor to the cockpit alongside the washroom, and a rest compartment with at least one berth for at least one pilot. The corridor alongside the washroom includes a mechanism separating the corridor from the cockpit and a door for blocking access to the passenger cabin. The rest compartment can be accessed from the access corridor to the cockpit, between the separation mechanism between the corridor and the cockpit and the corridor door. The washroom includes two access doors, a first access door for accessing the washroom from the access corridor to the cockpit in the area located between the separation mechanism between the corridor and the cockpit and the corridor door, and a second access door for accessing the washroom from the passenger cabin.

摘要翻译： 飞机的机身的前部包括驾驶舱，洗手间，盥洗室旁边的驾驶舱的通道走廊以及至少有一个至少一个飞行员的泊位的休息室。 洗手间旁边的走廊包括将走廊与驾驶舱分开的机构和用于阻止进入客舱的门。 休息室可以从通道走廊到驾驶舱，走廊与驾驶舱和走廊门之间的分离机构之间。 洗手间包括两个通道门，第一通道门，用于在走廊和驾驶舱与走廊门之间的分离机构之间的区域内从进入走廊进入洗手间到驾驶舱;以及第二检修门，用于进入洗手间 从客舱。

公开(公告)号：US08096505B2

公开(公告)日：2012-01-17

申请号：US12231289

申请日：2008-08-29

申请人： Arne Klarmann ,  Nick Chignell-Stapleton

发明人： Arne Klarmann ,  Nick Chignell-Stapleton

IPC分类号： B64D11/06

CPC分类号： B64C1/1469 ,  B64C2001/009

摘要： A deceleration device for a movable component in an aircraft, the device having a deformation component, wherein the deformation component includes a deformation tool, a deformation body with a deformable region, and a guide device. The deformation tool and the deformation body can be made to engage each other in such a manner by means of the guide device that in the case of movement of the deformation body and of the deformation tool relative to each other the deformable region of the deformation body can be deformed by the deformation tool.

摘要翻译： 一种用于飞行器中的可移动部件的减速装置，该装置具有变形部件，其中变形部件包括变形工具，具有可变形区域的变形体和引导装置。 可以通过引导装置使变形工具和变形体彼此接合，使得在变形体和变形工具相对于彼此移动的情况下变形体的可变形区域 可以通过变形工具变形。

公开(公告)号：US07770949B2

公开(公告)日：2010-08-10

申请号：US11923238

申请日：2007-10-24

申请人： James J. Kunda ,  Shannon J. Kupfer ,  Michael E. Renzelmann

发明人： James J. Kunda ,  Shannon J. Kupfer ,  Michael E. Renzelmann

IPC分类号： E05B15/02 ,  E05C1/06

CPC分类号： E05B47/0046 ,  B64C1/1469 ,  B64C2001/009 ,  Y10T292/096 ,  Y10T292/1021 ,  Y10T292/68 ,  Y10T292/696 ,  Y10T292/699

摘要： An aircraft door mechanism includes a solenoid connected to a support assembly. The solenoid displaces the latch pin between a solenoid energized and a solenoid de-energized position. A catch assembly rotatably connected to the support assembly is positioned to engage a 3½ degree or less taper portion of the latch pin in the solenoid energized position. When the latch pin moves to the solenoid de-energized position, a latch bolt supported by the door rotates the catch assembly. The latch bolt includes a distal bulbous end which multiplies the force applied to the door to rotate the catch assembly. If the latch pin is extended, a substantially greater force is required to force the latch pin to the solenoid de-energized position owing to the reduced taper of the latch pin. Authorized door entry is therefore easier and unauthorized door entry is made more difficult.

摘要翻译： 飞机门机构包括连接到支撑组件的螺线管。 电磁阀在螺线管通电和螺线管断电位置之间移动闩锁销。 可旋转地连接到支撑组件的卡盘组件被定位成在螺线管激励位置中接合闩锁销的3½度或更小的锥形部分。 当闩锁销移动到螺线管断电位置时，由门支撑的闩锁螺栓使锁扣组件旋转。 闩锁螺栓包括远端球形端，其将施加到门的力相乘以使捕捉组件旋转。 如果闩锁销延伸，则由于闩锁销的锥度减小，所以需要大大的力来将闩锁销强制到螺线管断电位置。 因此，门禁进入更为容易，未经授权的门禁进入更加困难。

公开(公告)号：US20090273487A1

公开(公告)日：2009-11-05

申请号：US11965203

申请日：2007-12-27

申请人： Daniel Ferro ,  Vincent Lautridou

发明人： Daniel Ferro ,  Vincent Lautridou

IPC分类号： G01C21/00 ,  G08B23/00

CPC分类号： B64D45/0015 ,  B64C1/1469 ,  B64C2001/009

摘要： An interconnecting apparatus for interconnecting a pilot station of an aircraft to at least one aircraft zone includes a device for communicating between the pilot station and the aircraft zone. The aircraft zone includes a device permitting a person present in the aircraft zone to identify themselves and a display device indicating a functional status of the aircraft. The pilot station includes a display device indicating a location of each person being identified in the aircraft zone.

摘要翻译： 用于将飞行器的飞行员站与至少一个飞行器区域相互连接的互连装置包括用于在飞行员飞行器区域和飞行器区域之间进行通信的装置。 飞机区域包括允许存在于飞行器区域中的人识别自身的装置和指示飞行器的功能状态的显示装置。 该试点站包括一个显示装置，指示在飞行器区域中识别的每个人的位置。