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公开(公告)号：US08579479B2
公开(公告)日：2013-11-12
申请号：US12996831
申请日：2009-06-19
申请人： Carsten Kohlmeier-Beckmann , Martin Griesbach , Bernhard Müller , Sonja Ferling , Andre Hessling , Sascha Lüder
发明人： Carsten Kohlmeier-Beckmann , Martin Griesbach , Bernhard Müller , Sonja Ferling , Andre Hessling , Sascha Lüder
IPC分类号： B64D47/02
CPC分类号： B64D47/06 , B64D2203/00 , F21S43/14 , F21S45/43 , F21S45/47 , F21V29/70 , F21V29/74 , F21V29/83 , F21W2107/30 , F21W2111/00 , F21Y2115/10
摘要： The warning lamp for an aircraft is provided with a housing (10) which possesses a light permeable cover (12) that is exposed to the surrounding air when the housing is mounted on the aircraft, with a frontal cover area and a rear cover area, a mounting element (44) to fasten the cover to a lower part (14) of the housing (10), wherein one edge (41) of the cover (12) is covered by an edge of the mounting element (44) and protrudes from it, a lamp with at least one LED (42,46,58,60), which is arranged within an area that is covered by the cover (12), and a cooling body (18) for the at least one LED (42,46,58,60), wherein the cooling body (18) possesses a cooling surface (32) that is exposed to the surrounding air when the housing (10) is mounted on the aircraft. The frontal cover area is formed by a frontal cover element (22) which is made from a light permeable first material. The rear cover area is formed by a rear cover element (28), which is made from a light permeable second material. The cooling body (18), while separating the frontal cover element (22) from the rear cover element (28), is arranged between them, wherein its cooling surface (32) is a part of the external contours of the cover (12) of the housing (10) that is given by the frontal and rear cover elements (22,28) and possesses an upper region (38) as well as adjacent, opposing side areas (40).
摘要翻译： 用于飞行器的警示灯设置有壳体（10），该壳体具有透光罩（12），当壳体安装在飞行器上时，该透光罩暴露于周围的空气，具有正面盖区域和后盖区域， 安装元件（44），用于将盖子紧固到壳体（10）的下部（14），其中盖（12）的一个边缘（41）被安装元件（44）的边缘覆盖并且突出 一种具有至少一个LED（42,46,58,60）的灯，其布置在由所述盖（12）覆盖的区域内，以及用于所述至少一个LED的冷却体（18） 42,46,58,60），其中所述冷却体（18）具有当壳体（10）安装在飞机上时暴露于周围空气的冷却表面（32）。 正面覆盖区域是由可透光的第一材料制成的前盖元件（22）形成的。 后盖区域由可透光的第二材料制成的后盖元件（28）形成。 冷却体（18）在将前盖元件（22）与后盖元件（28）分离的同时被布置在它们之间，其中其冷却表面（32）是盖子（12）的外部轮廓的一部分， 由前侧和后盖元件（22,28）给出并具有上部区域（38）以及相邻的相对的侧部区域（40）的壳体（10）。
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公开(公告)号：US07534016B2
公开(公告)日：2009-05-19
申请号：US11702001
申请日：2007-02-02
CPC分类号： B64C1/1484 , B64D2011/0061 , E06B9/24 , E06B2009/2464
摘要： A window unit for an aircraft with which individual lighting scenarios can be produced. In addition, an aircraft is equipped with at least one window unit. The window unit includes a window pane, which is coated with an electrically actuatable shading device for reducing incidental light entering through the window page. In addition, the window unit includes a control unit for operating the shading device as well as a lighting device for producing a light effect in the region of the window unit. In this connection, the control unit has an interface via which the control unit is connected to a network system of the aircraft for operation of the shading device. Likewise, the lighting device is coupled with the control unit, so that the lighting device can be operated with the network system of the aircraft via the interface of the control unit.
摘要翻译： 用于可以生产各种照明场景的飞机的窗单元。 另外，一架飞机配有至少一个窗单元。 窗户单元包括窗玻璃，其被涂覆有电致动阴影装置，用于减少通过窗页进入的附带光。 此外，窗单元包括用于操作遮光装置的控制单元以及用于在窗单元的区域中产生光效果的照明装置。 在这方面，控制单元具有接口，通过该接口，控制单元连接到飞行器的网络系统以用于遮蔽装置的操作。 同样地，照明装置与控制单元相连，使得照明装置可以通过控制单元的接口与飞行器的网络系统一起操作。
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公开(公告)号：US20070186477A1
公开(公告)日：2007-08-16
申请号：US11702001
申请日：2007-02-02
IPC分类号： E05F17/00
CPC分类号： B64C1/1484 , B64D2011/0061 , E06B9/24 , E06B2009/2464
摘要： A window unit for an aircraft with which individual lighting scenarios can be produced. In addition, an aircraft is equipped with at least one window unit. The window unit includes a window pane, which is coated with an electrically actuatable shading device for reducing incidental light entering through the window page. In addition, the window unit includes a control unit for operating the shading device as well as a lighting device for producing a light effect in the region of the window unit. In this connection, the control unit has an interface via which the control unit is connected to a network system of the aircraft for operation of the shading device. Likewise, the lighting device is coupled with the control unit, so that the lighting device can be operated with the network system of the aircraft via the interface of the control unit.
摘要翻译： 用于可以生产各种照明场景的飞机的窗单元。 另外，一架飞机配有至少一个窗单元。 窗户单元包括窗玻璃，其被涂覆有电致动阴影装置，用于减少通过窗页进入的附带光。 此外，窗单元包括用于操作遮光装置的控制单元以及用于在窗单元的区域中产生光效果的照明装置。 在这方面，控制单元具有接口，通过该接口，控制单元连接到飞行器的网络系统以用于遮蔽装置的操作。 同样地，照明装置与控制单元相连，使得照明装置可以通过控制单元的接口与飞行器的网络系统一起操作。
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公开(公告)号：US07186012B2
公开(公告)日：2007-03-06
申请号：US10888277
申请日：2004-07-09
IPC分类号： F21V7/04
CPC分类号： F21S8/02 , B60Q3/43 , B64D11/00 , B64D2011/0038 , F21V21/04 , F21V31/04 , F21Y2115/10 , G02B6/4298 , Y10S362/80
摘要： A lighting element has a light emitting diode that is installed in a light carrier. The lighting element has a light guide element that is optically coupled to the light emitting diode and the light guide element has a smaller light exit surface than the light emitting diode. With a plurality of such lighting elements it is possible to embody an effect lighting configuration for example in an aircraft cabin.
摘要翻译： 照明元件具有安装在光载体中的发光二极管。 照明元件具有与发光二极管光学耦合的导光元件，并且导光元件具有比发光二极管更小的光出射表面。 利用多个这样的照明元件，可以例如在飞机机舱中体现效果照明配置。
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公开(公告)号：US20060114683A1
公开(公告)日：2006-06-01
申请号：US11252447
申请日：2005-10-18
IPC分类号： F21V11/00
CPC分类号： B64D11/00 , B60K2370/343 , B60Q3/43 , B60Q3/44 , B60Q3/46 , B60Q3/745 , B64D2011/0038 , B64D2011/0053 , B64D2011/0061
摘要： In present-day passenger aircraft, fluorescent lamps in tubular form, are used as general illumination. An illumination unit for aircraft having a two-dimensional light source, an aperture which is at least partly translucent, and an attachment element. In this arrangement, the aperture is an interior fitting element of an aircraft cabin so that the entire illumination unit can be integrated in the aircraft cabin when the interior fitting element is installed. The flat design of the light source makes the installation of the light source possible in spaces of limited depth.
摘要翻译： 在当今的客机中，以管状形式的荧光灯被用作一般照明。 用于具有二维光源的飞行器的照明单元，至少部分半透明的孔和附接元件。 在这种布置中，孔是飞机机舱的内部装配元件，使得当安装内部装配元件时，整个照明单元可以集成在飞机机舱中。 光源的平面设计使得光源的安装可能在有限深度的空间中。
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公开(公告)号：US08348451B2
公开(公告)日：2013-01-08
申请号：US11776312
申请日：2007-07-11
IPC分类号： F21S8/02
CPC分类号： B60Q3/46 , B64D2011/0038 , B64D2203/00
摘要： Emergency cabin illumination for an aircraft, including: at least one cabin component of an aircraft and at least one emergency lighting device, the at least one emergency lighting device being arranged in the cabin component so that the emergency lighting device in its switched-off state has no contrast to its environment, and in the switched-on state of the emergency lighting device, the light emitted emerges from the cabin component.
摘要翻译： 一种用于飞机的紧急舱照明，包括：飞机的至少一个客舱部件和至少一个应急照明装置，所述至少一个应急照明装置布置在所述舱室部件中，使得所述应急照明装置处于关闭状态 与其环境没有对比，并且在应急照明装置的接通状态下，从舱室部件发出的光发射出来。
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公开(公告)号：US20110261577A1
公开(公告)日：2011-10-27
申请号：US12996831
申请日：2009-06-19
申请人： Carsten Kohlmeier-Beckmann , Martin Griesbach , Bernhard Müller , Sonja Ferling , Andre Hessling , Sascha Lüder
发明人： Carsten Kohlmeier-Beckmann , Martin Griesbach , Bernhard Müller , Sonja Ferling , Andre Hessling , Sascha Lüder
IPC分类号： F21S8/10
CPC分类号： B64D47/06 , B64D2203/00 , F21S43/14 , F21S45/43 , F21S45/47 , F21V29/70 , F21V29/74 , F21V29/83 , F21W2107/30 , F21W2111/00 , F21Y2115/10
摘要： The warning lamp for an aircraft is provided with a housing (10) which possesses a light permeable cover (12) that is exposed to the surrounding air when the housing is mounted on the aircraft, with a frontal cover area and a rear cover area, a mounting element (44) to fasten the cover to a lower part (14) of the housing (10), wherein one edge (41) of the cover (12) is covered by an edge of the mounting element (44) and protrudes from it, a lamp with at least one LED (42,46,58,60), which is arranged within an area that is covered by the cover (12), and a cooling body (18) for the at least one LED (42,46,58,60), wherein the cooling body (18) possesses a cooling surface (32) that is exposed to the surrounding air when the housing (10) is mounted on the aircraft. The frontal cover area is formed by a frontal cover element (22) which is made from a light permeable first material. The rear cover area is formed by a rear cover element (28), which is made from a light permeable second material. The cooling body (18), while separating the frontal cover element (22) from the rear cover element (28), is arranged between them, wherein its cooling surface (32) is a part of the external contours of the cover (12) of the housing (10) that is given by the frontal and rear cover elements (22,28) and possesses an upper region (38) as well as adjacent, opposing side areas (40).
摘要翻译： 用于飞行器的警示灯设置有壳体（10），该壳体具有透光罩（12），当壳体安装在飞行器上时，该透光罩暴露于周围的空气，具有正面盖区域和后盖区域， 安装元件（44），用于将盖子紧固到壳体（10）的下部（14），其中盖（12）的一个边缘（41）被安装元件（44）的边缘覆盖并且突出 一种具有至少一个LED（42,46,58,60）的灯，其布置在由所述盖（12）覆盖的区域内，以及用于所述至少一个LED的冷却体（18） 42,46,58,60），其中所述冷却体（18）具有当壳体（10）安装在飞机上时暴露于周围空气的冷却表面（32）。 正面覆盖区域是由可透光的第一材料制成的前盖元件（22）形成的。 后盖区域由可透光的第二材料制成的后盖元件（28）形成。 冷却体（18）在将前盖元件（22）与后盖元件（28）分离的同时被布置在它们之间，其中其冷却表面（32）是盖子（12）的外部轮廓的一部分， 由前侧和后盖元件（22,28）给出并具有上部区域（38）以及相邻的相对的侧部区域（40）的壳体（10）。
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8.发明授权公开(公告)号：US07905638B2
公开(公告)日：2011-03-15
申请号：US11779572
申请日：2007-07-18
IPC分类号： B64D47/02
CPC分类号： F21V5/00 , B60Q3/43 , B60Q3/54 , B60Q3/745 , B60Q2500/10 , B64D2011/0038 , F21V2200/30 , F21Y2115/10
摘要： An aircraft cabin panel includes an aircraft cabin lighting seamlessly integrated with the panel. The aircraft cabin lighting includes at least one light emitting diode or LED and a diffuser. The diffuser includes a first body with a first index of refraction and a plurality of second bodies which are arranged in the first body and having a second index of refraction.
摘要翻译： 飞机机舱面板包括与面板无缝集成的飞机机舱照明。 飞机舱照明包括至少一个发光二极管或LED和漫射器。 扩散器包括具有第一折射率的第一主体和布置在第一主体中并且具有第二折射率的多个第二主体。
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公开(公告)号：US07081835B2
公开(公告)日：2006-07-25
申请号：US10455035
申请日：2003-06-05
IPC分类号： G08B21/00
CPC分类号： H05B37/02 , H05B37/0254 , H05B37/029
摘要： A control device for the actuation of lamps in particular for internal aircraft lighting, wherein the control device (1) has an input (18) for the supply of an input signal and a plurality of outputs (21–28) for passing output signals to connected lamps (L1–L8). In the control device (1) a signal processing module (8–12) is preferably formed by a microprocessor and a preferably freely programmable electronic memory (13–17). The signal processing module (8–12) produces the output signals from the input signal in accordance with a conversion instruction deposited in the memory (13–17), wherein different conversion instructions can be stored in the memory (13–17) for output signals belonging to different outputs (21–28).
摘要翻译： 一种用于特别用于内部飞行器照明的灯的致动的控制装置，其中所述控制装置（1）具有用于提供输入信号的输入端（18）和用于将输出信号传递到 连接灯（L 1 -L 8）。 在控制装置（1）中，信号处理模块（8-12）优选地由微处理器和优选地可自由编程的电子存储器（13-17）形成。 信号处理模块（8-12）根据存储在存储器（13-17）中的转换指令从输入信号产生输出信号，其中不同的转换指令可被存储在存储器（13-17）中用于输出 属于不同输出的信号（21-28）。
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10.发明申请System and method for detecting faults in an aircraft electrical power system 审中-公开用于检测飞机电力系统故障的系统和方法公开(公告)号：US20050013075A1
公开(公告)日：2005-01-20
申请号：US10894869
申请日：2004-07-19
CPC分类号： H02J13/0024 , Y02E60/7823 , Y04S40/122
摘要： An aircraft electrical power system includes a monitored load (e.g. group of lightbulbs) connected through a sub-system power unit and a power distribution center to a power bus. A current monitor of the power distribution center is able to detect a total failure of the sub-system power unit and its connected monitored load, but is not able directly to detect the failure of a single load component (e.g. single lightbulb). The sub-system power unit includes a fault detector able to detect a fault or failure of a single load component (e.g. single lightbulb) in the monitored load. When the fault detector detects such a fault, the sub-system power unit generates a modulated current signal in the current drawn by the sub-system power unit, with a magnitude greater than the detection threshold of the power distribution center, which thus recognizes the detected fault based on the modulated current signal.
摘要翻译： 飞机电力系统包括通过子系统电力单元连接的监控负载（例如，灯泡组）和配电中心到电力总线。 配电中心的电流监视器能够检测到子系统电源单元及其连接的监视负载的全部故障，但是不能直接检测单个负载组件（例如，单个灯泡）的故障。 子系统功率单元包括故障检测器，其能够检测所监视的负载中的单个负载组件（例如单个灯泡）的故障或故障。 当故障检测器检测到这种故障时，子系统功率单元以由系统功率单元抽出的电流产生调制电流信号，其幅度大于配电中心的检测阈值，从而识别出 基于调制电流信号检测到故障。
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