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公开(公告)号：US20170233058A1
公开(公告)日：2017-08-17
申请号：US15312374
申请日：2015-05-29
申请人： Zodiac Aerospace
发明人： Yannick Brunaux , Sebastien Sivignon , Alison Gill , Britta Appolt , Claude Martin , Ramon Blauwhoff
CPC分类号： B64C1/18 , B64C1/00 , B64C2001/0027 , B64D11/00 , B64D11/0007 , B64D11/003 , B64D47/08 , B64D2011/0061 , B64D2011/0076
摘要： Embodiments of the present invention provide systems and methods for allowing use of what has traditionally been a cargo area of a passenger aircraft to be used as a lower deck passenger cabin. Various modifications to the aircraft are described, as well as various features to be added in order to enhance the passenger experience. For example, there may be provided a lowered technical floor (32), stairs or other passageways (50) provided at both ends of the lower deck cabin, a window replacement technique, an alternative way of storing cabin luggage, or any combination thereof.
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公开(公告)号：US09688379B2
公开(公告)日：2017-06-27
申请号：US13630287
申请日：2012-09-28
发明人： Maik Koch , Matthias Breuer
CPC分类号： B64C1/1469 , B64C1/14 , B64C1/18 , B64C1/32
摘要： An actuation device for opening an emergency exit flap of a cockpit door is provided. The actuation device comprises a support structure, at least two securing elements, an actuation element and a deflection mechanism. The support structure is configured so as to be fastened to the emergency exit flap. The securing elements are integrated into the support structure and are configured so as to fasten the actuation device, and thus the emergency exit flap, to the cockpit door. The actuation element is connected to the support structure. Therein, the deflection mechanism connects the securing elements to the actuation element in such a way that a force which is exerted on the actuation element is diverted in such a way that the securing elements are released from the cockpit door.
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53.发明申请公开(公告)号：US20170166291A1
公开(公告)日：2017-06-15
申请号：US15375478
申请日：2016-12-12
发明人： Bernard Guering
摘要： A zone provided between the forward pressure bulkhead in an aircraft and the floor. The nose section of the aircraft in which the flat surface pressure bulkhead including at least one transverse frame comprises at least two rods, of which one of the front ends is attached to the bulkhead and/or the frame and the other rear end is attached to a structural element, the two rods further apart from the front to the rear, thus providing a work space. Therefore, the rods provide a more comfortable work area while picking up part of the loads from the bulkhead to the floor.
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公开(公告)号：US09636901B2
公开(公告)日：2017-05-02
申请号：US14262428
申请日：2014-04-25
IPC分类号： B29C65/00 , B32B37/00 , B65H81/00 , H01F41/12 , B31C3/00 , B32B38/04 , C08J5/00 , B32B3/12 , B29C70/08 , B29C70/86 , B29D24/00 , B29D99/00 , B32B3/08 , B29C73/06 , B64C1/18 , B32B5/12 , B32B5/18 , B32B5/22 , B32B5/24 , B32B5/26 , B32B7/04 , B32B7/12 , B32B3/02 , B32B3/04 , B32B3/14 , B29K105/08 , B29L31/30 , B29L31/60
CPC分类号： B32B38/04 , B29C70/086 , B29C70/088 , B29C70/865 , B29C73/06 , B29D24/005 , B29D99/0021 , B29K2105/0881 , B29L2031/3076 , B29L2031/608 , B32B3/02 , B32B3/04 , B32B3/08 , B32B3/12 , B32B3/14 , B32B5/12 , B32B5/18 , B32B5/22 , B32B5/245 , B32B5/26 , B32B7/045 , B32B7/12 , B32B2038/047 , B32B2260/021 , B32B2260/046 , B32B2262/0269 , B32B2262/101 , B32B2262/106 , B32B2307/50 , B32B2307/544 , B32B2605/18 , B64C1/18 , Y02T50/43 , Y02T50/46 , Y10T156/1056 , Y10T428/24149 , Y10T428/24157
摘要： A Sandwich panel with a core structure, in particular with a honeycomb-shaped core structure, and plane-parallel cover layers applied to both sides of this core structure, to form a floor surface in a fuselage airframe of an aircraft, the core structure having at least one recess into which at least one reinforcing structure is integrated, wherein the at least one reinforcing structure is formed with at least one core, said core having at least one recess into which a stopper is introduced, into which at least one attachment element can be introduced to attach at least one further component to the sandwich panel, and a plurality of prepreg strips which each have a uniform fiber running direction being wound around the core. In addition, the invention relates to a method for the production of a sandwich panel according to the invention.
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公开(公告)号：US09623914B2
公开(公告)日：2017-04-18
申请号：US13599932
申请日：2012-08-30
摘要： A covering system for an interior space of a vehicle comprises at least one surface element and at least one sealing element. The surface element comprises an upper surface and at least one bounding edge extending at an angle to the upper surface. The surface element furthermore comprises at least one recess, which runs at least adjacent to the bounding edge. The sealing element has an extent corresponding at least partly with the at least one bounding edge, and a shape corresponding at least partly with the recess of the surface element.
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公开(公告)号：US20170105245A1
公开(公告)日：2017-04-13
申请号：US15288347
申请日：2016-10-07
发明人： Thilo Rochell
摘要： A heated floor panel system for an aircraft, the floor panel system comprising a floor panel element including a panel structure and a panel heater device, a temperature sensor device for detecting the temperature at the floor panel element, and a connector device connected to the floor panel element, wherein the connector device comprises a power link for providing an electric power connection between the panel heater device and an electric power supply, and a data link for providing a data connection between the temperature sensor device and a control unit. An object of the present disclosure, to provide a floor panel system including a floor panel element which has a possibly simple construction and which can be used independently from the connector device, is achieved in that the temperature sensor device is located in the connector device and connected to the floor panel element via a thermal conductor element.
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57.发明授权Unitary panel for the floor of a vehicle, floor, and vehicle including such a unitary panel 有权车辆，地板和车辆的地板上的单一面板包括这样一个单一的面板公开(公告)号：US09586671B2
公开(公告)日：2017-03-07
申请号：US14389186
申请日：2013-03-28
申请人： SOGECLAIR S.A.
发明人： Mathieu Deloubes
CPC分类号： B64C1/18 , B64C1/061 , B64C1/20 , B64D11/04 , B64D11/06 , B64D11/0696 , Y02T50/46 , Y10T29/49622
摘要： The invention relates to a unitary floor panel (1) for a means of transportation, comprising a self-supporting plate (2) having a smallest dimension, called the thickness, extending along a first direction of the self-supporting plate (2), and two larger dimensions extending along two directions that are orthogonal to each other and orthogonal to the thickness; the self-supporting plate (2) having two opposite sides, called main sides, that extend substantially parallel to the two orthogonal directions; characterized in that the panel comprises at least one beam (5) securely fastened to the self-supporting plate (2) and having an axis of elongation parallel to at least one first main side of the self-supporting plate (2), each beam (5) being designed to increase the flexural strength of the unitary panel (1) along the axis of elongation of the beam (5).
摘要翻译： 本发明涉及一种用于运输工具的整体地板（1），包括一个自支撑板（2），其具有沿自支撑板（2）的第一方向延伸的称为厚度的最小尺寸， 以及沿着彼此正交并与厚度正交的两个方向延伸的两个较大尺寸; 自支撑板（2）具有两个相对的侧面，称为主侧面，其基本上平行于两个正交方向延伸; 其特征在于，所述面板包括牢固地紧固到所述自支撑板（2）并且具有平行于所述自支撑板（2）的至少一个第一主侧的伸长轴线的至少一个梁（5），每个梁 （5）被设计成沿着梁（5）的伸长轴增加整体板（1）的弯曲强度。
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公开(公告)号：US09566759B2
公开(公告)日：2017-02-14
申请号：US14471161
申请日：2014-08-28
申请人： The Boeing Company
CPC分类号： B32B3/266 , B64C1/18 , B64C2001/009 , Y10T29/49622 , Y10T428/24273
摘要： A decompression panel for use in an aircraft assembly that includes a body portion including a top edge and a bottom edge, and a front surface and a rear surface opposing the front surface. A plurality of openings are formed in the body portion, and a first stiffening member is formed on the rear surface below the plurality of openings. The first stiffening member extends from the rear surface towards the top edge such that the plurality of openings are at least partially obstructed by the first stiffening member.
摘要翻译： 一种用于飞机组件的减压板，包括：主体部分，其包括顶部边缘和底部边缘;以及前表面和与前表面相对的后表面。 多个开口形成在主体部分中，第一加强构件形成在多个开口下方的后表面上。 第一加强构件从后表面朝向顶部边缘延伸，使得多个开口至少部分地被第一加强构件阻挡。
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公开(公告)号：US09517829B2
公开(公告)日：2016-12-13
申请号：US14449543
申请日：2014-08-01
CPC分类号： B64C1/061 , B64C1/18 , F16B7/0406 , F16B7/22
摘要： An aircraft fuselage structure is disclosed having an outer skin, a support structure arrangement with frame elements, and a floor structure arrangement with floor support struts, the floor structure arrangement connected to the support structure arrangement via connection parts. A connection exists between the floor structure arrangement and the support structure arrangement, with a clamping element on the connection part and a locking element on the connection part. The clamping element includes a longitudinal section having a first and a second end. The first end is pivotally attached to the connection part. The second end includes a transverse section, the locking element including at least one locking groove, and the clamping element pivotable between an engagement position in which the transverse section engages the locking groove, and a released position, in which the transverse section is disengaged therefrom.
摘要翻译： 公开了一种具有外皮，具有框架元件的支撑结构装置和具有地板支撑支柱的地板结构装置的飞行器机身结构，所述地板结构装置经由连接部分连接到支撑结构装置。 在地板结构布置和支撑结构布置之间存在连接，在连接部分上具有夹紧元件，在连接部分上具有锁定元件。 夹紧元件包括具有第一端和第二端的纵向截面。 第一端枢转地连接到连接部。 第二端包括横截面，锁定元件包括至少一个锁定槽，并且夹紧元件可在横向部分与锁定槽接合的接合位置之间枢转，以及释放位置，在该释放位置，横向部分从该位置脱离 。
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公开(公告)号：US20160340020A1
公开(公告)日：2016-11-24
申请号：US15149966
申请日：2016-05-09
申请人： Goodrich Corporation
发明人： George Owens , Kevin E. Roach , Kurt M. Tauscher
CPC分类号： B64C1/18 , B64C1/40 , B64C2001/0072 , B64D13/08 , F24D13/024 , Y02B30/26
摘要： An aircraft heated floor panel includes a first support layer, a second support layer, and a heating layer located between the first support layer and the second support layer. An aircraft floor panel includes a floor panel body and a removal feature that provides a mechanism for the aircraft floor panel to be removed from an attached aircraft structure.
摘要翻译： 飞机加热地板镶板包括第一支撑层，第二支撑层和位于第一支撑层和第二支撑层之间的加热层。 飞机地板镶板包括地板面板主体和移除特征，其提供用于飞行器地板面板从附接的飞行器结构中移除的机构。
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