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81. 发明公开

EP3246244A1 A SYSTEM FOR LOCKING A FOLDABLE WING TIP ON A WING END OF AN AIRCRAFT 有权
标题翻译：一种用于在飞机的翼端上锁定可折叠翼尖的系统
公开(公告)号：EP3246244A1
公开(公告)日：2017-11-22
申请号：EP16170603.1
申请日：2016-05-20
申请人： Airbus Operations GmbH
发明人： Winkelmann, Christoph , Rupp, Johannes
IPC分类号： B64C3/56
CPC分类号： B64C3/56 , B64D47/02 , B64F5/60
摘要： A system for locking a foldable wing tip on a wing end of an aircraft comprises at least one engagement means (10), at least one locking device (2) comprising a support (4), a latch element (14) rotatably held in the support (4) and a lock element (32) movably held on the support (4), a latch drive means (38) coupled with the latch element (14) of the at least one locking device (2) for selectively rotating the latch element (14) at least to an open position, a closed position and a test position, a lock drive means (40) coupled with the lock element (32) of the at least one locking device (2) for selectively varying a distance of the lock element (32) to the latch element (14) between a neutral position and a locking position, wherein the support (4) comprises a receiving space (6) extending into an insertion opening designed for receiving the engagement means (10). The latch element (14) comprises a circumferential surface section (16) that selectively covers the insertion opening (8) in an open position and uncovers the insertion opening in a closed position of the latch element (14). The latch element (14) comprises at least one locking recess (48) arranged on a circumferential path of motion (15) for engaging with the lock element in the closed position of the latch element and the locking position of the lock element. The rotatable latch element further comprises at least one protrusion (62, 66, 68, 70) on the circumferential path of motion (15), which acts as a stop for the lock element (32). The system further comprises a signaling means indicating a correct function when the lock element (32) rests on the at least one protrusion (62, 66, 68, 70).
摘要翻译：一种用于锁定飞机机翼末端上的可折叠翼梢的系统，包括至少一个接合装置（10），至少一个锁定装置（2），其包括支撑件（4），闩锁元件（14）（4）和可移动地保持在所述支撑件（4）上的锁定元件（32）;与所述至少一个锁定装置（2）的所述锁定元件（14）耦合的锁定驱动装置（38），用于选择性地旋转所述锁定件（14）至少到打开位置，关闭位置和测试位置;锁定驱动装置（40），与所述至少一个锁定装置（2）的锁定元件（32）耦合，用于选择性地改变所述锁定元件（32）在所述锁定元件（14）处于中性位置和锁定位置之间，其中所述支撑件（4）包括延伸到设计用于接收所述接合装置（10）的插入开口中的接收空间（6）。闩锁元件（14）包括周向表面部分（16），该周向表面部分在打开位置选择性地覆盖插入开口（8），并且在闩锁元件（14）的关闭位置打开插入开口。锁定元件（14）包括布置在周向运动路径（15）上的至少一个锁定凹部（48），用于在锁定元件的关闭位置和锁定元件的锁定位置与锁定元件接合。可转动的闩锁元件还包括在圆周运动路径（15）上的至少一个突起（62,66,68,70），其用作锁定元件（32）的止动件。该系统还包括当锁定元件（32）搁置在至少一个突起（62,66,68,70）上时指示正确功能的信号装置。

82. 发明公开

EP3210887A1 VEHICLE CABIN WAYFINDING ASSEMBLY 有权
标题翻译：汽车客舱装配组装
公开(公告)号：EP3210887A1
公开(公告)日：2017-08-30
申请号：EP17152565.2
申请日：2017-01-23
申请人： The Boeing Company
发明人： VALENTINE, William H. Jr
IPC分类号： B64D11/00
CPC分类号： B64D11/00 , B60Q3/00 , B64D47/02 , B64D2011/0038 , B64D2045/007 , B64D2203/00 , F21V7/0008 , F21V7/0083
摘要： A vehicle cabin wayfinding assembly is configured to be secured within an internal cabin of a vehicle. The vehicle cabin wayfinding assembly may include a placard 102 having a front face 106, and at least one directional reflector 104 offset from the front face of the placard. The directional reflector(s) defines one or more indicia 104a-104d, and is configured to directionally reflect light that is emitted from a light source 218 into an application zone.
摘要翻译：车厢引路组件被构造成被固定在车辆的内部车厢内。车厢引路组件可以包括标牌102，标牌102具有前表面106和至少一个偏离标牌正面的定向反射器104。定向反射器限定一个或多个标记104a-104d，并且被配置成将从光源218发射的光定向地反射到施加区域中。

83. 发明公开

EP3193496A1 CONTROLLER, CONTROL METHOD, AND FLIGHT VEHICLE DEVICE 有权
标题翻译：控制器，控制方法和飞行器装置
公开(公告)号：EP3193496A1
公开(公告)日：2017-07-19
申请号：EP15851321.8
申请日：2015-08-24
申请人： Sony Corporation
发明人： SABE, Kohtaro , TANAKA, Kayoko , SUZUKI, Kousuke , MASUDA, Masaaki , KAKINUMA, Takekazu , HAYASHI, Kazunori
IPC分类号： H04N5/238 , B64C13/18 , B64C13/20 , B64C27/04 , B64C39/02 , B64D47/04 , B64D47/08 , G03B7/093 , G03B15/00 , G03B15/02 , G03B15/03 , G03B15/05 , G03B17/00 , G03B17/56 , H04N5/225 , H04N5/232
CPC分类号： B64D47/02 , B64C27/08 , B64C39/024 , B64C2201/027 , B64C2201/108 , B64C2201/127 , B64C2201/145 , B64C2201/146 , B64D47/08 , B64D2203/00 , G03B7/093 , G03B15/00 , G03B15/006 , G03B15/02 , G03B15/03 , G03B15/05 , G03B17/00 , G03B17/56 , G05D1/0094 , H04N5/2256 , H04N5/23222 , H04N5/2354 , H05B33/0854
摘要： [Object] To provide a control device which enables a flight vehicle device to obtain a highly precise image.
[Solution] Provided is the control device including an illuminating control unit configured to adjust a light amount of an illuminating device according to an inclination of a body of a flight vehicle device that has an imaging device configured to photograph a photographing target and the illuminating device configured to illuminate the photographing target.
摘要翻译：本发明的目的是提供一种使飞行器装置能够获得高精度图像的控制装置。所述控制装置包括照明控制单元，所述照明控制单元被配置为根据飞行器装置的主体的倾斜来调节照明装置的光量，所述飞行器装置具有被配置为拍摄拍摄目标的成像装置和照明装置被配置为照射拍摄目标。

84. 发明公开

EP3193228A2 METHOD OF AUTONOMOUSLY OPERATING AN AIRCRAFT LIGHTING SYSTEM AND AUTONOMOUS EXTERIOR AIRCRAFT LIGHT 有权
标题翻译：自动操作飞机照明系统和自主外部飞机灯的方法
公开(公告)号：EP3193228A2
公开(公告)日：2017-07-19
申请号：EP17151149.6
申请日：2017-01-12
申请人： Goodrich Corporation
发明人： LECLEAR, Ronald J. , HESSLING-von HEIMENDAHL, Andre
IPC分类号： G05D1/00 , B64D47/02 , B64D47/06 , H05B37/02
CPC分类号： B64D47/02 , B60Q1/00 , B64D47/06 , H05B37/0227
摘要： A method of autonomously operating an aircraft lighting system is disclosed. The aircraft lighting system includes at least one autonomously operated exterior aircraft light (6, 8, 10, 12, 14, 16, 18, 20, 22), with each of the at least one autonomously operated exterior aircraft light having at least two operating states. The method comprises the steps of determining a momentary value of at least one of a group of aircraft operation parameters consisting of height above ground, rate of descent, ground speed, and weight on wheels; for each of the at least one autonomously operated exterior aircraft light, selecting a particular operating state from the at least two operating states depending on the momentary value of the at least one of the group of aircraft operation parameters; and controlling each of the at least one autonomously operated exterior aircraft light in accordance with the particular operating state selected.
摘要翻译：公开了一种自主操作飞机照明系统的方法。该飞行器照明系统包括至少一个自主操作的外部飞行器灯（6,8,10,12,14,16,18,20,22），并且至少一个自主操作的外部飞行器灯中的每一个具有至少两个操作状态。该方法包括以下步骤：确定由高于地面的高度，下降率，地面速度和车轮重量组成的一组飞机操作参数中的至少一个的瞬时值; 对于所述至少一个自主操作的外部飞行器灯中的每一个，根据所述一组飞行器操作参数中的至少一个的瞬时值从所述至少两个操作状态中选择特定操作状态; 以及根据所选择的特定操作状态来控制所述至少一个自主操作的外部飞行器灯中的每一个。

85. 发明公开

EP2476616A3 Aircraft emergency lighting 有权转让
标题翻译：飞机应急照明
公开(公告)号：EP2476616A3
公开(公告)日：2017-07-05
申请号：EP12150968.1
申请日：2012-01-12
申请人： Saf-t-Glo Limited
发明人： Rust, Daniel
IPC分类号： B64D11/00 , H02J9/06 , B64D47/02 , B64D45/00
CPC分类号： B64D11/00 , B64D47/02 , B64D2011/0038 , B64D2045/007 , B64D2203/00 , H02J9/065
摘要： Emergency lighting for an aircraft has a primary power source for light units 9 provided by the normal aircraft power supply 11 and a secondary power source provided by power supply units 15 operable to back-up the primary power source. Each light unit 9 may have its own power supply unit 15 operable to power the light unit 9 in an emergency if the normal aircraft power supply fails or is otherwise unable to power the emergency lighting. Each power supply unit 15 includes one or more electric double layer capacitors 15a that are charged whenever the normal aircraft power supply is operational to provide the primary power source. The useful life of the electric double layer capacitors 15a may be prolonged by reducing the capacitor voltage when the emergency lighting is switched off.
摘要翻译：飞机的应急照明具有用于由普通飞机电源11提供的灯单元9的主要电源和由可用于备份主电源的电源单元15提供的次要电源。每个灯单元9可以具有其自己的供电单元15，该供电单元15可操作以在紧急情况下在紧急情况下给灯单元9供电，如果正常的飞行器电源失效或否则不能给应急照明供电。每个电源单元15包括一个或多个双电层电容器15a，每当正常的飞行器电源运行时提供主电源就被充电。当紧急照明关闭时，通过降低电容器电压可以延长双电层电容器15a的使用寿命。

86. 发明公开

EP3181459A1 EXTERIOR AIRCRAFT LIGHT UNIT AND AIRCRAFT COMPRISING THE SAME 有权
标题翻译：外部飞机发光单元和包含该发动机的飞机
公开(公告)号：EP3181459A1
公开(公告)日：2017-06-21
申请号：EP15200651.6
申请日：2015-12-17
申请人： Goodrich Lighting Systems GmbH
发明人： Hessling-von Heimendahl, Andre , Jha, Anil Kumar , Trinschek, Robert
IPC分类号： B64D47/02
CPC分类号： H05B33/0893 , B64D47/02 , B64D2203/00 , F21V7/0091 , F21V13/04 , F21V17/06 , F21W2107/30 , F21Y2115/10
摘要： An exterior aircraft light unit (2) includes a support plate (4), an LED (6), mounted to the support plate, a near end of life detector (8) for sensing a light output level of the LED, the near end of life detector being mounted to the support plate, and a transparent optical element (10) for shaping an output light intensity distribution of the exterior aircraft light unit, wherein the transparent optical element jointly encases the LED and the near end of life detector, with light from the LED reaching the near end of life detector through the transparent optical element.
摘要翻译：一种外部飞行器照明单元（2），包括支撑板（4），安装到支撑板的LED（6），用于感测LED的光输出水平的寿命检测器（8）的近端，近端寿命检测器安装在支撑板上;以及透明光学元件（10），用于对外部飞行器照明单元的输出光强度分布进行整形，其中透明光学元件共同包围LED和寿命近端检测器，来自LED的光通过透明光学元件到达生命探测器的近端。

87. 发明公开

EP3168159A1 EXTERIOR AIRCRAFT LIGHT UNIT 有权
标题翻译：外部飞机发光单元
公开(公告)号：EP3168159A1
公开(公告)日：2017-05-17
申请号：EP15194543.3
申请日：2015-11-13
申请人： Goodrich Lighting Systems GmbH
发明人： HESSLING-von HEIMENDAHL, Andre , GAUSEPOHL, Andreas
IPC分类号： B64D47/02 , F21V31/03 , F21W101/06 , B01D53/26 , F21Y115/10
CPC分类号： F21V31/005 , B01D53/263 , B01D53/28 , B01D2259/4575 , B64D47/02 , B64D47/04 , B64D47/06 , F21S45/30 , F21V3/00 , F21V29/89 , F21V31/03 , F21W2107/30 , F21Y2101/00 , F21Y2115/10
摘要： An exterior aircraft light unit (2) comprises a housing (12) defining an interior space (14) for accommodating at least one light source (4); and a hygroscopic material (24), which is arranged inside the interior space (14) for absorbing water and/or moisture from inside the interior space (14).
摘要翻译：一种外部飞机照明单元（2）包括限定用于容纳至少一个光源（4）的内部空间（14）的外壳（12）; 和布置在内部空间（14）内用于从内部空间（14）内部吸收水分和/或湿气的吸湿材料（24）。

88. 发明公开

EP3118123A1 EXTERIOR HELICOPTER LIGHT UNIT AND METHOD OF OPERATING AN EXTERIOR HELICOPTER LIGHT UNIT 有权
标题翻译：华盛顿州胡志明市首府华盛顿州胡志明市
公开(公告)号：EP3118123A1
公开(公告)日：2017-01-18
申请号：EP15177240.7
申请日：2015-07-17
申请人： Goodrich Lighting Systems GmbH
发明人： Schoen, Christian , Hessling-von Heimendahl, Andre , Jha, Anil Kumar , Tsibadze, Christo
IPC分类号： B64D47/04
CPC分类号： B64D47/02 , B60Q1/1423 , B60Q1/245 , B64D47/04 , B64D2203/00 , F21V5/04 , F21V7/00 , F21Y2115/10 , H05B33/0854 , H05B37/0227
摘要： An exterior helicopter light unit (2) with a dynamic output light intensity distribution includes a plurality of LEDs (30), and an optical system (32) for shaping the output light intensity distribution from light emitted by the plurality of LEDs (30), wherein each of the plurality of LEDs (30) contributes to the output light intensity distribution in an LED-specific output direction region, wherein at least a portion of the plurality of LEDs (30) are individually dimmable, with a level of dimming for each of said portion of the plurality of LEDs (30) in operation being set depending on a distance of the exterior helicopter light unit (2) to ground (200) in the respective LED-specific output direction region.
摘要翻译：具有动态输出光强度分布的外部直升机灯单元（2）包括多个LED（30）和用于使由多个LED（30）发射的光形成输出光强度分布的光学系统（32）其中所述多个LED（30）中的每一个有助于LED特定输出方向区域中的输出光强度分布，其中所述多个LED（30）的至少一部分是可单独调光的，其中每个LED 所述多个LED（30）的所述部分在操作中根据所述外部直升机灯单元（2）在各个LED特定输出方向区域中的接地（200）的距离来设定。

89. 发明授权

EP2663162B1 LED flash light and method for indicating near-end-of-life status of such an LED flash light 有权
标题翻译：用于显示所述近端的例如LED闪光灯光源的寿命LED闪光灯和方法
公开(公告)号：EP2663162B1
公开(公告)日：2017-01-11
申请号：EP12167435.2
申请日：2012-05-10
申请人： Goodrich Lighting Systems GmbH
发明人： Müller, Bernhard
IPC分类号： H05B37/03 , H05B33/08
CPC分类号： H05B37/03 , B64D47/02 , B64D2203/00 , H05B33/0803 , H05B33/0818 , H05B33/0851 , H05B33/0893

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