Abstract: An aircraft beacon light unit has an operating light emission distribution. The operating light emission distribution has a first light emission opening angle of at least 150° in a first cross-sectional plane, and a second light emission opening angle of at most 180° in a second cross-sectional plane orthogonal to the first cross-sectional plane. The aircraft beacon light unit is configured in such a way that it is mountable to an aircraft with the first cross-sectional plane being oriented in a vertical direction and the second cross-sectional plane being oriented in a horizontal direction, and the first light emission opening angle extends at least 75° both above and below the second cross-sectional plane.

Abstract: An exterior aircraft image projector includes at least one light source, providing a light output in operation; an optical system configured for transforming the light output of the at least one light source into a light beam and projecting said light beam onto the ground below the aircraft and the of the aircraft; a photo detector arranged to detect a brightness level (Iambient) of the ground or the exterior and configured to provide a corresponding brightness signal; and a controller, coupled to the photo detector and the at least one light source configured to control an intensity of the light output of the at least one light source as a function of the brightness level (Iambient), as provided by the photo detector via the brightness signal.

Abstract: The light device of a motor vehicle comprises a light unit (4) and a cover (2). The light unit (4) comprises a light guide (7) with a front surface (8) for the exit of light rays (10) from the light guide (7) situated opposite the cover (2), a rear surface (9) comprising unbinding elements (73) configured to reflect light rays (10) towards the front surface (8), and at least one binding surface (71) to bind light rays (10) emitted by the light source (6) associated with the binding surface (71) to the light guide (7). The light device further comprises a carrier (5) situated opposite the rear surface (9) of the light guide (7) and configured to reflect light rays (10) that have escaped from the light guide (7) through the rear surface (9) back to the light guide (7). The cover (2) comprises at least one impermeable region (22) preventing light rays (10) from passing out of the cover (2), and at least one permeable region (21) to allow light rays (10) to pass through the cover (2).

Abstract: A cover for an exterior aircraft light includes a lens cover structure, attachable to an exterior aircraft light housing and configured to close the exterior aircraft light housing, wherein the lens cover structure has an inside and an outside and is at least partially made of transparent material; and a wear indicator, attached to the inside of the lens cover structure, the wear indicator having a contrasted pattern visible from the outside of the lens cover structure through the transparent material.

Abstract: A modular light assembly having a control housing surrounding a power driver and at least one modular component. The modular component includes two side portions, a plurality of ribs extending between the two side portions to form a grated portion, and a flat portion configured to receive a COB LED. The lighting assembly may also comprise a video assembly having a camera and control circuitry provided within the lighting and video assembly for remotely controlling the camera.

Abstract: A cast concrete durable light fixture design and assembly that will allow in-ground lighting features for roadways, pathways and architectural features providing a simple installation for a drive over in-grade or in-ground lighting fixture. The cast concrete design enables curves and shapes to be manufactured as easily as straight or linear configurations.

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

Abstract: A set of exterior aircraft lights, comprises a main landing light, which comprises at least one main landing light source and is configured for emitting a main landing light beam around a main landing light beam direction (L), and at least one of a taxi light and a runway turn-off light. The taxi light is configured for emitting a taxi light beam around a taxi light beam direction (T) and for emitting a first auxiliary landing light beam around a first auxiliary landing light beam direction (AL1), wherein the first auxiliary landing light beam direction (AL1), when projected onto a vertical plane, is angled downwards between 5° and 15° with respect to the straight ahead direction. The runway turn-off light is configured for emitting a runway turn-off light beam around a runway turn-off light beam direction (Ra, Rb).

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

Abstract: A lighting assembly is provided with a housing defining a cavity with a rearward opening and a forward opening formed opposite the rearward opening along a longitudinal axis. A plurality of light sources is supported by the housing and disposed within the rearward opening. A first lens is supported by the housing with a plurality of optics each aligned with one of the plurality of light sources to receive light and collimate the received light within the housing, wherein the first lens is formed of glass. A second lens is disposed within the forward opening of the housing to receive the collimated light and generate an illumination pattern.

Abstract: An aircraft passenger reading light include comprises: a light source arrangement having a plurality of rows of reading light sources, with each of the rows having a plurality of reading light sources for passenger-specific illumination of a plurality of seats of a seating row of an aircraft and with the plurality of rows having different illumination directions in a longitudinal direction (L) of the aircraft, whereinach of the light sources first and second electrical terminals; first and second power supply connectors; and a multi-state switching arrangement having a plurality of switching states. The first power supply connector is coupled to the first electrical terminals of the plurality of reading light sources. The second power supply connector is coupled to the second electrical terminals of the plurality of reading light sources via the multi-state switching arrangement.

Abstract: An exterior helicopter light is configured to be mounted to a helicopter, in particular to an underside of the helicopter, the helicopter having a longitudinal axis (A). The exterior helicopter light comprises: a first set of light sources configured for emitting, in operation, light of a first color into a at least one rear sector of a ground below the helicopter, the at least one rear sector spatially extending around a projection of a rear portion of the helicopter onto the ground; and second set of light sources configured for emitting, in operation, light of a second color, which differs from the first color, into at least two forward sectors of the ground below the helicopter.

Abstract: A replaceable light head for an exterior aircraft light includes a mounting structure for attaching the replaceable light head to the exterior aircraft light; a power terminal, coupleable to an internal power supply of the exterior aircraft light; at least one light source, coupled to the power terminal for receiving power from the internal power supply of the exterior aircraft light; a data interface, coupleable to a controller of the exterior aircraft light; and a memory, coupled to the data interface and configured to receive and store usage data of the internal power supply of the exterior aircraft light.

Abstract: A networked infrastructure is described that includes a set of programmed computing nodes, each node being configured with a processor and non-transitory computer readable media including computer-executable instructions that, when executed by the processor, facilitate a social security number registry server carrying out a method that provides an individual with the ability to remotely approve or disapprove, in real-time, the use of his/her social security number (SSN) by a relying party server.

Abstract: An aircraft beacon light for an aircraft wing with a foldable wing tip includes a housing, a lens cover, and at least one light source arranged between the housing and the lens cover, wherein the aircraft beacon light is configured to emit flashes of red light in operation, and wherein the housing and the lens cover are shaped to embed the aircraft beacon light into a hinge assembly coupling the foldable wing tip to a main wing portion of the aircraft wing.

Abstract: A modular light assembly having a control housing surrounding a power driver and at least one modular component. The modular component includes two side portions, a plurality of ribs extending between the two side portions to form a grated portion, and a flat portion configured to receive a COB LED. The lighting assembly may also comprise a video assembly having a camera and control circuitry provided within the lighting and video assembly for remotely controlling the camera.

Abstract: A light assembly includes a core, a light source, and a functional layer. The core extends along a centerline, and includes a base end, a distal end, a first side spanning axially between the base and distal ends, and a second side opposite the first side and spanning axially between the base and distal ends. The second side includes an unbinding element axially extending partially between the base and distal ends. The light source is adapted to emit light rays into the core at the base end. The functional layer is laterally spaced from the first side, axially extends partially between the base and distal ends, and is axially aligned to the unbinding element.

Abstract: A light beam forming module, in particular in the vehicle external lighting system, is in the form of a monolithic body formed of a plurality of contiguous cross-sectional segments, each of which includes an entrance surface facing the light source, an exit surface, and a first total internal reflection surface and at least another total internal reflection surface. A first total internal reflection surface is positioned downstream of the entrance surface, and at least one further total internal reflection surface has a shaped optical structure formed thereon.

Abstract: A method of operating an aircraft cabin illumination system, having a plurality of light modules with a set spatial distribution across an aircraft cabin, includes receiving an image; mapping the image to the set spatial distribution of the plurality of light modules; generating an illumination command set, including an operating command for each of the plurality of light modules, on the basis of the mapping of the image to the set spatial distribution of the plurality of light modules; and issuing the illumination command set to the plurality of light modules.

Abstract: The invention relates to a communication device of a motor vehicle (X), comprising an imaging camera (2) of a scene image (11) connected to control electronics (1), to which a DMD (7) is connected, the mirror surface (70) of which is preceded by optics (3), whereby the mirror surface (70) is functionally associated with a secondary imaging unit (5) having an optical sensor (50) adapted to receive a selected part of the light (32) from the scene image (11) reflected by a selected part of the mirrors of the mirror surface (70) of the DMD (7). The DMD (7) is part of the vehicle lighting device (0) in which an illumination unit (4) is arranged towards the mirror surface (70) of the DMD (7), the illumination unit (4) being adapted to illuminate controllably at least a part of the mirror surface (70) of the DMD (7) and to emit the desired light output beam (30).