Goodrich Lighting Systems Patente

An aircraft beacon light (2) includes a light source carrier (4), wherein the light source carrier (4) comprises a plurality of connection fields (6), with the plurality of connection fields (6) forming at least two polygonal connection structures (8a, 8b, 8c, 8d, 8e, 8f, 8g, 8h, 8i, 8j) on the light source carrier (4); and a plurality of LED modules (10), with the plurality of LED modules (10) being arranged along a particular one of the at least two polygonal connection structures (8a, 8b, 8c, 8d, 8e, 8f, 8g, 8h, 8i, 8j) and with each of the plurality of LED modules (10) being coupled to a respective connection field (6) of said particular one of the at least two polygonal connection structures (8a, 8b, 8c, 8d, 8e, 8f, 8g, 8h, 8i, 8j).

A method of assigning a passenger (5) to a lavatory (6a-6d) within an aircraft passenger cabin (2), wherein the aircraft passenger cabin (2) comprises at least two lavatories (6a-6d), each having a waiting queue (60a-60d), and wherein the aircraft passenger cabin (2) is divided into at least two spatial zones (8a-8d), includes: receiving a lavatory assignment request (48) from a passenger (5); based on a seat location of said passenger (5), determining a particular spatial zone (8a-8d) of the aircraft passenger cabin (2) which includes the seat location of said passenger (5); and based on the particular spatial zone (8a-8d), adding the passenger (5) to the waiting queue (60a-60d) of a particular lavatory (6a-6d), associated with the particular spatial zone (8a-8d). The configuration of the at least two spatial zones (8a-8d) is variable and it is based on a plurality of zone configuration parameters including a queue length of each of the waiting queues (60a-60d) of the at least two lavatories (6a-6d).

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An aircraft overhead passenger service unit (110) comprises a plurality of oxygen masks (12) for supplying oxygen to aircraft passengers in an emergency situation; and at least two different oxygen mask storage portions (25a, 25b), which are spaced apart from each other in a longitudinal direction (L). The plurality of oxygen masks (12) are stored in the at least two different oxygen mask storage portions (25a, 25b). The aircraft overhead passenger service unit (110) further comprises an oxygen mask controller (26), which is switchable between at least two different configurations. The at least two different oxygen mask storage portions (25a, 25b) are individually associated with the at least two different configurations, with each of the at least two different configurations effecting a release of only the oxygen masks (12) of the associated oxygen mask storage portion (25a. 25b) in the emergency situation.

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A passenger service unit including an ion emitter is disclosed herein. The passenger service unit includes an air outlet assembly, a control unit (308) electronically coupled to the air distribution box, an air gasper assembly (402) coupled to the air distribution box, and an ion emitter coupled to the air gasper assembly (402) and electronically coupled to the control unit (308), wherein the ion emitter is configured to be controlled by the control unit (308).

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An aircraft light (2) comprises: a support element (4), supporting at least one light source (6); an injection molded optical element (8), made of light transmissive silicone rubber; and a layer of light transmissive silicone rubber (12) arranged between at least a portion of the injection molded optical element (8) and at least a portion (4b) of the support element (4). The layer of light transmissive silicone rubber (12) provides adhesion between the injection molded optical element (8) and the support element (4).

A navigation light system (200) for an unmanned aerial vehicle (100), such as a multicopter type unmanned aerial vehicle, includes: a plurality of light emission units (20), wherein each of the plurality of light emission units (20) has a unit-specific light emission direction (24) and is configured to provide a light output (30) around the unit-specific light emission direction (24) and wherein each of the plurality of light emission units (20) includes a multi-color light source (22) capable of emitting red light, green light, and white light; wherein the plurality of light emission units (20) are arranged to jointly provide a navigation light pattern (80) around the unmanned aerial vehicle (100) and wherein the light outputs (30) of adjacent light emission units (20) have an overlap (40); and wherein the navigation light system (200) is configured to operate each of the plurality of light emission units (20) depending on a relation between a momentary flight direction (120) of the unmanned aerial vehicle (100) and the respective unit-specific light emission direction (24), with the navigation light pattern (80) around the unmanned aerial vehicle (100) providing a red sector (82), a green sector (84), and a white sector (86) in accordance with the momentary flight direction (120) of the unmanned aerial vehicle (100) and with the overlap (40) of the light outputs of adjacent light emission units at a border between the red sector (82) and the green sector (84) providing a white flight direction indicator light output (88).

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A lighting device (2) includes a circuit board (4); an LED (6), soldered to the circuit board (4); an optical element (8; 9), supported by the circuit board (4) and positioned for re-directing at least part of the light in operation emitted by the LED (6); and a magnetic coupling (10) between the circuit board (4) and the optical element (8; 9).

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A method of determining operating conditions of an exterior aircraft light (2) comprising at least one light source (4) includes: operating the at least one light source (4) of the exterior aircraft light (2); repeatedly detecting light with a light detector (12), which is located at the exterior aircraft light (2) and configured for providing light detection values (I); determining a smallest light detection value (I<min>) provided by the light detector (12) within a first period of time, and storing said smallest light detection value (I<min>) as an element of a series of smallest light detection values (I<min>); and evaluating the light detection values (l) and the series of smallest light detection values (I<min>) for detecting erosion of an optical component (8) of the exterior aircraft light (2), for detecting the presence of ambient light (14) and/or for detecting the presence of fog and/or clouds (20) in front of the exterior aircraft light (2).

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A helicopter lighting system (30) comprises a docking station (32), configured to be mounted to a helicopter (10) and configured for allowing an unmanned aerial vehicle (100) to dock to and to separate from the docking station (32); and an unmanned aerial vehicle (100), in particular an unmanned aerial vehicle (100) of a multicopter type, configured for docking to and separating from the docking station (32), the unmanned aerial vehicle (100) including at least one lighting device (120), configured for illuminating at least one target object (300) or area (310) which is visible from the helicopter (10).

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Exterior aircraft light (2) comprises a dome-shaped light transmissive cover (4), a light emission assembly (12), and an interface assembly (14). The light emission assembly (12) comprises a light emission tower portion (16), having a cover-facing end (16a) and an opposite aircraft-facing end (16b) and having a hollow channel (22) extending between the aircraft-facing end (16b) and the cover-facing end (16a), a platform portion (17), and at least one light source (18) and at least one optical element (20), arranged on the platform portion (17). The interface assembly (14) extends through the hollow channel (22) of the light emission tower portion (16) and comprises an elevated base (32), which is configured for mechanically supporting and electrically connecting an electric component (34), the electric component (34) being at least one of a data reception component, a data transmission component, and a data generation component. The interface assembly (14) further comprises at least one signal line (52), which extends from the elevated base (32) through the interface assembly (14).

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