Goodrich Lighting Systems

A passenger service unit fixing element (6) for releasably fixing a passenger service unit (2, figure 2) in a passenger cabin (102, figure 2) of an aircraft (100, figure 1) comprises a clamping body (7) and a locking element (30) that is rotatably arranged in the clamping body (7). The clamping body (7) comprises at least one clamp (8a, 8b), and each of the at least one clamp (8a, 8b) comprises a coupling portion (14a, 14b) for being coupled to the passenger service unit (2) and a clamping portion (12a, 12b) for being clamped to a support member (4) provided in the passenger cabin (102). The clamping portion (12a, 12b) comprises two clamp arms (16, 18) that are elastically movable with respect to each other between a clamped configuration, in which the support member (4) is clampable between the two clamp arms (16, 18), and a released configuration, in which the clamping portion (12a, 12b) is detachable from the support member (4). The locking element (30) is rotatable between a locked position, in which the locking element (30) locks the clamp arms (16, 18) in the clamped configuration, and an unlocked position, in which the locking element (30) allows the clamp arms (16, 18) to move from the clamped configuration into the released configuration.

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.

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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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …