Abstract: An optics support system for an aircraft light comprises: a multi-layer support board, having a main plane of extension; an LED arranged on the multi-layer support board; a first set of leg stands, positioned around the LED, wherein the first set of leg stands provides first abutment surfaces for arranging an optical element, having a corresponding set of legs, over the LED in a first orientation; and a second set of leg stands, positioned around the LED. The second set of leg stands provides second abutment surfaces for arranging the optical element over the LED in a second orientation; and the first abutment surfaces and the second abutment surfaces are at different heights in a z-dimension of the multi-layer support board, orthogonal to the main plane of extension.

Abstract: A light module for an elongated interior aircraft light comprises a plurality of light sources, which are configured for emitting light of different colors and which are arranged next to each other, forming an array of light sources extending between a first end and a second end along a longitudinal direction (LD). The plurality of light sources include a first light source, which is arranged at the first end, and a second light source, which is arranged at the second end. The first and second light sources are those from the plurality of light sources that result in a difference of the illuminating properties between the first and second light sources being the smallest difference that is possible for all potential pairs of light sources formed from the plurality of light sources.

Abstract: An interior aircraft lighting assembly comprises: at least one infrared lighting device for emitting infrared light; at least one further lighting device for emitting visible light; a lighting assembly controller for controlling an operation of the at least one infrared lighting device and of the at least one further lighting device; a supplementary infrared lighting device controller; and a power supply network, which is configured for supplying electric power from the lighting assembly controller to the at least one further lighting device. The supplementary infrared lighting device controller is tapped into the power supply network. The lighting assembly controller is configured to provide an electric trigger pulse on the power supply network for activating the at least one infrared lighting device.

Abstract: An aircraft light comprises a light source support board, having a light source side and a back side; and a light source, arranged on the light source side of the light source support board; wherein the light source support board comprises a first metallic layer, the first metallic layer forming conductive traces on the light source side of the light source support board; an isolating layer; a second metallic layer, wherein the isolating layer is arranged between the first metallic layer and the second metallic layer and isolates the second metallic layer from the first metallic layer; and a support board core layer. A cavity is provided in the support board core layer.

Abstract: An aircraft beacon light includes a plurality of primary light sources for emitting light into at least two spatial sectors, wherein the at least two spatial sectors include a forward sector and at least one of an aft sector, a starboard lateral sector, and a portside lateral sector; and a light transmissive cover, which covers the plurality of primary light sources. The plurality of primary light sources are arranged and configured for providing an FAR-compliant aircraft beacon light output of the aircraft beacon light, in case of the light transmissive cover being in a non-eroded state. The aircraft beacon light also includes at least one booster light source for selectively emitting a booster light output into the forward sector. The at least one booster light source is controllable independently of the plurality of primary light sources.

Abstract: An aircraft light includes a light source support board; at least one light source, arranged on a light source side of the light source support board, the at least one light source being arranged to provide an aircraft light output of the aircraft light; a light transmission opening through the light source sup-port board, the light transmission opening extending between the light source side of the light source support board and a back side of the light source support board; an electronics accommodation space on the back side of the light source support board; a first auxiliary support board, arranged in the electronics accommodation space; a second auxiliary support board, arranged in the electronics accommodation space; and an opto-electronic component, arranged on the second auxiliary support board and oriented towards the light transmission opening.

Abstract: An elongated aircraft cabin light for illuminating a passenger cabin of an aircraft from a ceiling of the passenger cabin comprises: a row arrangement of a plurality of light modules, extending along a longitudinal direction (L) of the elongated aircraft cabin light. Each of the plurality of light modules comprises at least one light source. The plurality of light modules include a plurality of intermediate light modules and, on at least one end of the row arrangement, an end light module. Each of the plurality of intermediate light modules is configured for emitting a downward light output and at least one lateral light output towards at least one lateral side.

Abstract: An aircraft overhead passenger service unit, which is configured to be mounted in a passenger cabin of an aircraft above a passenger seating space, comprises a visual sign structure extending downward from the aircraft overhead passenger service unit. The visual sign structure comprises a signal light and a wall illumination light. The signal light is arranged on a first side of the visual sign structure facing rearward. The signal light comprises at least one first switchable light source. The wall illumination light is arranged on a second side of the visual sign structure facing forward. The wall illumination light comprises at least one second switchable light source and a light directing element. The at least one second switchable light source and the light directing element are arranged to provide a wall illumination light output towards a lateral side of the aircraft overhead passenger service unit.

Abstract: An aircraft light comprises: at least one light source for providing an aircraft light output; a light sensor for detecting a performance level of the aircraft light output; and a sensor cap, arranged over the light sensor and defining a cavity for accommodating the light sensor. The sensor cap has a layered structure comprising: a cap-shaped support layer; a first coating layer, wherein the first coating layer is made of a first metal and is arranged on an inner side of the cap-shaped support layer; and a second coating layer. The second coating layer is made of a second metal and is arranged on the first coating layer.

Abstract: An aircraft light comprises: a support element, supporting at least one light source; an injection molded optical element, made of light transmissive silicone rubber; and a layer of light transmissive silicone rubber arranged between at least a portion of the injection molded optical element and at least a portion of the support element. The layer of light transmissive silicone rubber provides adhesion between the injection molded optical element and the support element.

Abstract: An exterior aircraft light comprises a housing defining an interior space; a light output generation unit comprising at least one light source; power supply electronics, coupled to the light output generation unit for driving a light output of the exterior aircraft light and a draining device for draining the interior space. At least one of the light output generation unit and the power supply electronics is arranged within the interior space. The draining device comprises a first drainage tube for receiving fluid, a second drainage tube for receiving fluid; and a fluid discharge port for discharging fluid out of the housing. Each of the first and second drainage tubes comprises a valve mechanism for selectively sealing and opening the respective drainage tube with respect to the interior space.

Abstract: An interior aircraft lighting assembly comprises: at least one infrared lighting device for emitting infrared light; at least one further lighting device for emitting visible light; a lighting assembly controller for controlling an operation of the at least one infrared lighting device and of the at least one further lighting device; a supplementary infrared lighting device controller; and a power supply network, which is configured for supplying electric power from the lighting assembly controller to the at least one further lighting device. The supplementary infrared lighting device controller is tapped into the power supply network. The lighting assembly controller is configured to provide an electric trigger pulse on the power supply network for activating the at least one infrared lighting device.

Abstract: An exterior aircraft light comprises a housing defining an interior space; a light output generation unit comprising at least one light source; power supply electronics, coupled to the light output generation unit for driving a light out-put of the exterior aircraft light; and a draining device for draining the interior space. The draining device comprises a first drainage tube for receiving fluid, which is to be drained from the interior space; a second drain-age tube for receiving fluid, which is to be drained from the interior space; and a fluid discharge port for discharging fluid out of the housing, wherein the fluid discharge port is in fluid communication with the first drainage tube and with the second drainage tube. Each of the first drainage tube and the second drainage tube comprises a valve mechanism for selectively sealing and opening the respective drainage tube with respect to the interior space.

Abstract: An exterior aircraft light comprise at least one light emission assembly that includes at least one light source; a cup-shaped reflector; and a light transmissive cover for the cup-shaped reflector. The at least one light source is arranged at a bottom portion of the cup-shaped reflector and a light output opening is provided at a top portion of the cup-shaped reflector. The light transmissive cover comprises a lid portion, extending across the light output opening of the cup-shaped reflector; and a column-shaped light collimating portion, extending from the lid portion into the cup-shaped reflector towards the at least on light source and comprising a light collimation surface facing the at least one light source. The lid portion comprises, on at least one side thereof, a light dispersing profile.

Abstract: An aircraft reading light with a color-tunable reading light output includes: a white light source for emitting white light; a colored light source for emitting colored light; and an optical element, which is arranged for directing colored light that is emitted by the colored light source onto the white light source for being diffusely reflected at the white light source. The colored light source is controllable independently from the white light source.

Abstract: An aircraft passenger reading light, which is operable in at least two predetermined configurations, comprises: a light source; an optical element; and an actuation mechanism, which is configured to modify a distance between the light source and the optical element. The distance (D) between the light source and the optical element differs in the at least two predetermined configurations and a spatial extension of the illumination, which results from the light output of the light source and the optical element, differs in the at least two predetermined configurations.

Abstract: A multi mode aircraft beacon light comprises a mounting portion for mounting the multi mode aircraft beacon light to an aircraft fuselage; at least one visible light source for emitting a visible beacon light output; a plurality of infra-red light sources for emitting an infrared beacon light output; an orientation sensor; and a controller, coupled to the orientation sensor for receiving an orientation sensor signal from the orientation sensor. The controller is configured to determine a mounting orientation of the multi mode aircraft beacon light from the orientation sensor signal, wherein the mounting orientation is indicative of whether the multi mode aircraft beacon light has an upper fuselage mounting position or a lower fuselage mounting position; and to selectively operate the plurality of infrared light sources, depending on the mounting orientation of the multi mode aircraft beacon light.

Abstract: An interior aircraft lighting assembly comprises: at least one infrared lighting device for emitting infrared light; at least one further lighting device for emitting visible light; a lighting assembly controller for controlling an operation of the at least one infrared lighting device and of the at least one further lighting device; a supplementary infrared lighting device controller; and a power supply network, which is configured for supplying electric power from the lighting assembly controller to the at least one further lighting device. The supplementary infrared lighting device controller is tapped into the power supply network. The lighting assembly controller is configured to provide an electric trigger pulse on the power supply network for activating the at least one infrared lighting device.

Abstract: An aircraft light comprises at least one light source and a local electric power supply for supplying electric power to the at least one light source. The local electric power supply comprises a power supply housing, which is produced by additive manufacturing and comprises a compartment accommodating power supply electronics and at least one hollow cavity, which is delimited from the compartment. The compartment is filled with a potting material. The aircraft light further comprises a plurality of electric connections extending from the power supply electronics through the potting material to the at least one light source for supplying electric power to the at least one light source, thus enabling an aircraft light output of the aircraft light.

Abstract: An aircraft passenger service unit includes infrared sensor configured for detecting infrared radiation and for providing a corresponding sensor output, and a controller, which is configured for receiving and evaluating the sensor output provided by the infrared sensor. The infrared sensor is an infrared sensor array configured for detecting infrared radiation emitted within a plurality of spatial sectors covering a detection area below the aircraft passenger service unit; and the infrared sensor array is configured for detecting the infrared radiation individually for each spatial sector and for providing individual sensor signals for the plurality of spatial sectors. The infrared sensor array is configured such that each passenger seat arranged within the detection area is covered by at least two of the plurality of spatial sectors, respectively; and the controller is configured for determining a passenger seating position within a passenger seat from the individual sensor signals.