Goodrich Lighting Systems Patente

An interior aircraft lighting assembly (2) comprises: at least one infrared lighting device (22a, 22b, 22c) for emitting infrared light; at least one further lighting device (4, 26a, 26b, 26c) for emitting visible light; a lighting assembly controller (12) for controlling an operation of the at least one infrared lighting device (22a, 22b, 22c) and of the at least one further lighting device (4, 26a, 26b, 26c); a supplementary infrared lighting device controller (36); and a power supply network, which is configured for supplying electric power from the lighting assembly controller (12) to the at least one further lighting device (4, 26a, 26b, 26c). The supplementary infrared lighting device controller (36) is tapped into the power supply network. The lighting assembly controller (12) is configured to provide an electric trigger pulse on the power supply network for activating the at least one infrared lighting device (22a, 22b, 22c). The supplementary infrared lighting device controller (36) is coupled to the at least one infrared lighting device (22a, 22b, 22c) and is configured to enable power flow to the at least one infrared lighting device (22a, 22b, 22c) in response to detecting the electric trigger pulse, provided by the lighting assembly controller (12) on the power supply network; and the supplementary infrared lighting device controller (36) is configured to cause the at least one infrared lighting device 22a, 22b, 22c) to emit infrared light for an infrared lighting duration, which is longer than a duration of the electric trigger pulse.

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An exterior aircraft light (1) comprises a housing (8) defining an interior space (9); a light output generation unit (3) comprising at least one light source (2); power supply electronics (10), coupled to the light output generation unit (3) for driving a light output of the exterior aircraft light (1) and a draining device (12) for draining the interior space (9). At least one of the light output generation unit (3) and the power supply electronics (10) is arranged within the interior space (9). The draining device (12) comprises a first drainage tube (14a) for receiving fluid (26), a second drainage tube (14b) for receiving fluid (26); and a fluid discharge port (19) for discharging fluid (26) out of the housing (8). Each of the first and second drainage tubes (14a, 14b) comprises a valve mechanism (15a, 15b) for selectively sealing and opening the respective drainage tube (14a, 14b) with respect to the interior space (9). Each valve mechanism (15a, 15b) comprises a valve portion (16a, 16b) and a sealing element (18a, 18b), arranged in the valve portion (16a, 16b) of the respective drainage tube (14a, 14b). The sealing element (18a, 18b) is movable within the valve portion (16a, 16b) under the influence of gravity. The valve portion (16a, 16b) and the sealing element (18a, 18b) are shaped and dimensioned such that the sealing element (18a, 18b), driven by gravity, opens the respective drainage tube (14a, 14b), when the respective drainage tube (14a, 14b) is oriented in a draining orientation; and seals the respective drainage tube (14a, 14b) in an air-tight manner, when the respective drainage tube (14a, 14b) is oriented in a sealing orientation.

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An aircraft beacon light (2) comprises an annular light source support (6) having a plurality of light passing portions (6a); a plurality of light sources (4), arranged on the annular light source support (6) for a radially outwards emission of light flashes; a light detector (10) for sensing a light output level of at least a subset of the plurality of light sources (4); and at least one optical element (20) for shaping a beacon light output from light emitted by the plurality of light sources (4), the at least one optical element (20) having at least one light guiding portion (20b) for capturing stray light (7) from at least said subset of the plurality of light sources (4) and for guiding said stray light (7) through the plurality of light passing portions and towards the light detector (10).

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An exterior aircraft light (2) with integrated light output monitoring includes a light source support (4); at least one light source (6), arranged on an outward facing side (40) of the light source support (4); an aperture (12) in the light source support (4); a light collection surface (90), arranged to direct an output monitoring light portion (22) of the light, emitted by the at least one light source (6), through the aperture (12) in a predefined angular range with respect to the light source support (4); a light detector (20), arranged on a back side (42) of the light source support (4); and a total internal reflection optical element (14), arranged to direct the output monitoring light portion (22), having travelled through the aperture (12) in the predefined angular range with respect to the light source support (4), to the light detector (20) via total internal reflection.

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An aircraft light (2) includes a support board (4); a light source (6), arranged on the support board (4); an optical element (8; 8'; 12; 14), arranged over the light source (6); and a kinematic coupling fixture (20), establishing a fixed position of the optical element (8; 8'; 12; 14) with respect to the support board (4).

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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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