Abstract: A rear position light-emitting diode (LED) light module for use on an aircraft. The light module includes a single printed circuit board (PCB), at least one light emitting diode attached to a first surface of the PCB and a single reflector and baffle device attached to the PCB. The baffle device provides an illumination pattern having a predefined angular pattern in the first plane. The illumination pattern does not overlap with light illuminated by port and starboard position lights of the aircraft. The baffle device includes a base section being planar, the base section comprises a cavity, first and second side sections attached to a first surface of the base section on opposing sides of the cavity, the first and second side sections intersect the first plane but not the second plane and a plurality of snap fittings attached to a second side of the base section.

Abstract: A laser light reflection device for an aircraft-installed laser apparatus with which, when a function check is performed on the aircraft-installed laser apparatus by emitting laser light from a parked aircraft to a body exterior, the emitted laser light can be reflected in a desired direction safely and efficiently. A reflection mirror is capable of autorotation about at least an in-plane horizontal axis thereof, and a support ring is attached to the reflection mirror to be capable of rotating about an in-plane vertical axis and the in-plane horizontal axis of the reflection mirror. A laser pointer unit formed by inserting a laser pointer into a sleeve pipe is attached to the support ring so as to be oriented toward an in-plane of the reflection mirror. A guide scope is attached to the support ring such that an optical axis thereof matches an optical axis of the laser pointer unit.

Abstract: Escape path marking for an aircraft having a plurality of photoluminescent elements glow in the dark and of which each has a carrier element that is provided for attaching to a subsurface, characterized in that the carrier element has connecting edges on one or both end sides, the edges having an arc-shaped progression or having at least two sections not extending perpendicular to an orientation axis of the carrier element disposed perpendicularly on a cross section in the region of the connecting edge, the orientation axes of two carrier elements disposed successively enclosing an angle with each other.

Abstract: A light for an aircraft comprises a holder for carrying a first group of light emitting diodes arranged along a curvilinear line and a first reflector having an elliptic reflective partial surface defining a plurality of focal points forming a first curvilinear focal line coinciding with the light emitting sites of the first group of light emitting diodes and second focal point or curvilinear focal line. The light further includes a second optical unit comprising a single further focal point or curvilinear focal line that coincides with the second focal point or focal line of the first reflector. The light further includes a second group of light emitting diodes displaced axially with respect to the first light emitting diodes, which emit light that bypasses the second focal point or focal line of the first reflector of the first optical unit.

Abstract: An aircraft light comprises a housing (24), at least one light source (32) to be cooled, the at least one light source (32) being arranged in the housing (24), a heat sink element (26) thermally coupled to the at least one light source (32) and defining a cooling surface (36) exposable to a cooling airstream (52) for the cooling airstream (52) to flow along the cooling surface (36) in a flow direction. The cooling surface (36) extends between upstream and downstream end portions (40,42) spaced apart in the flow direction and means for generating a pressure difference between the upstream and downstream end portions (40,42) of the cooling surface. Due to the pressure difference, a cooling airstream (52) flowing along the cooling surface (36) is created.

Abstract: An aircraft light for emitting light in a desired spatial angular region and with a desired light distribution, comprises a reflector having an upper reflector portion and a lower reflector portion both being symmetrical to a plane. A first row of LEDs are face away from the reflector. A second row of LEDs face towards the reflector. Each of the upper and lower portions of the reflector comprises first, second, and third reflective surfaces with the first reflective surface being convexly shaped, the second reflective surface being substantially flat, and the third reflective surface being partially parabolically shaped.

Abstract: An aircraft light consists of a housing containing a light source, a heat sink element forming at least part of the exterior surface of the housing and an auxiliary thermal capacitor that is thermally decoupled from the heat sink element. A thermally expandable medium is coupled to the heat sink element and operates to thermally decouple the light source from the heat sink element and thermally couple the light source to the auxiliary thermal capacitor and vice versa, depending on the actual temperature of the heat sink element.

Abstract: The present invention is concerned with a modular lighting system having a casing containing a lamp, as well as its power and control circuits fitted within a wing and a flush fitting glazing unit.

Abstract: A lighting assembly for movable control surfaces of a vehicle. The light assembly includes a lens, a plurality of light-emitting diodes (LEDs) and a housing that receives the plurality of LEDs and the lens. The housing of the light assembly is received within the movable control surface, such that the lens is flush with a surface of the movable control surface. The light assembly includes a plurality of reflectors. The plurality of LEDs is rotatably mounted within the housing. The light assembly includes a controller that controls the position of the LEDs relative to the housing, based on a received control signal.

Abstract: A luminous vehicle glazing, containing: a first sheet containing a mineral or an organic glass having a first main face, a second main face, and an injection edge; a peripheral light source with an emitting face, which faces the injection edge; a guided-light extracting element; a peripheral functional element, bonded to the first sheet, which is fluid-tight, including a cavity for placing the peripheral light source; a covering element, which covers the cavity and the peripheral light source, which is fluid-tight, and which is selected from i) a cap combined with an interfacial element, for interfacial fluid-tightness or ii) a fluid-tight sealing mastic covering the peripheral light source and sealing the peripheral functional element. In addition, a method of manufacturing the luminous vehicle glazing.

Abstract: A light for an aircraft comprises a holder for carrying a plurality of light emitting diodes arranged along a curvilinear line and a first optical unit comprising an elliptic reflective partial surface defining a plurality of focal points forming a first curvilinear focal line extending along the light emitting sites of the light emitting diodes, and a plurality of second focal points. The light further includes a second optical unit comprising a single further focal point or a plurality of further focal points forming a further curvilinear focal line. The plurality of the second focal points of the first optical unit coincide and are identical to the single further focal point of the second optical unit or are located along the further curvilinear focal line of the second optical unit.

Abstract: An aircraft lamp includes a housing capable of being attached to a body of an aircraft; a discharge lamp; a reflector which reflects visible light from the discharge lamp; a light transmissive cover which transmits reflected light from the reflector to a front side of the housing; a lamp socket connected electrically to the discharge lamp and an igniter which activates the discharge lamp; and a high-voltage electrical power line that electrically connects the lamp socket with the igniter. The discharge lamp, the reflector, the light transmissive cover, the lamp socket, and the igniter are provided within the housing. A heat insulating air layer is provided between the lamp socket and the igniter. The high-voltage electrical power line is provided so as to pass through the heat insulating air layer.

Abstract: A lighting assembly for movable control surfaces of a vehicle. The light assembly includes a lens, a plurality of light-emitting diodes (LEDs) and a housing that receives the plurality of LEDs and the lens. The housing of the light assembly is received within the movable control surface, such that the lens is flush with a surface of the movable control surface. The light assembly includes a plurality of reflectors. The plurality of LEDs is rotatably mounted within the housing. The light assembly includes a controller that controls the position of the LEDs relative to the housing, based on a received control signal.

Abstract: A window intended to be assembled over an opening defined in an outside wall having on the one hand an outer partition and on the other hand an inner partition. This window includes a glazing, means making it possible to hold the glazing in the opening of the outside wall, while ensuring a watertightness at the outer partition, and a connection crosspiece between the outer partition and the inner partition. The crosspiece is implemented so as to make it possible to guide light having passed through the glazing toward the inner partition. Means making it possible to diffuse the light guided by the crosspiece are arranged at the inner partition.

Abstract: A lighting system for an emergency exit from an occupied space: an array of lighting elements located around the emergency exit to illuminate the exit and facilitate egress for an occupant of the space; a control unit; and sensors to detect one or more trigger conditions and actuate the lighting elements in response to a first trigger condition from any of the sensors, the sensors comprising: an impulse detector operable to send a signal to the control unit indicating that the impulse detector has experienced an impulse; and a roll and/or pitch detector operable to send a signal to the control unit indicating that the roll and/or pitch detector has experienced roll and/or pitch, wherein upon detection of the first trigger condition the control unit actuates one or more of the lighting elements to illuminate the exit.

Abstract: An aircraft wingtip device comprises illumination means arranged to project light onto interior and exterior surfaces of the wingtip device.

Abstract: Emergency lighting for an aircraft has a primary power source for light units provided by the normal aircraft power supply and a secondary power source provided by power supply units operable to back-up the primary power source. Each light unit may have its own power supply unit operable to power the light unit in an emergency if the normal aircraft power supply fails or is otherwise unable to power the emergency lighting. Each power supply unit includes one or more electric double layer capacitors that are charged whenever the normal aircraft power supply is operational to provide the primary power source. The useful life of the electric double layer capacitors may be prolonged by reducing the capacitor voltage when the emergency lighting is switched off.

Abstract: AN LED lighting device of an aircraft for maneuvers of landing, and/or take-off, and/or taxiing, and/or searching comprising: one or more light-emitting modules including a light-emitting semiconductor device configured for emitting a light radiation; a supporting substrate carrying the light-emitting semiconductor device; a curved reflector having a concave reflecting surface and defining a plane of emission, wherein the concave reflecting surface has a semiparabolic shape obtained by sectioning a semiparaboloid along two mutually parallel cutting planes, and is arranged facing the light-emitting semiconductor device in such a way as to collect the light radiation and generate a radiation reflected through the plane of emission.

Abstract: The present invention is a cargo lighting system with a plurality of light heads mounted to a support bar. The support bar is divided into a plurality of interlocking segments and supported by stringer engaging components and supplemental support members. The cargo lighting system includes a master control box which allows light heads to be controlled by a master switch or with individual zone controls. The cargo lighting system is easily disassembled and packed in protective cases for transport and storage.

Abstract: An aircraft navigation light comprises a base and circuit board in thermal contact with the base. White and colored LEDs mount on the circuit board. A reflector-shade placed adjacent the LEDs reflects light from the LEDs in desired directions and shades other directions from view of selected LEDs. A light transmissive cover sealed to the base, encloses the circuit board, LEDs and reflector-shade. Temperature responsive circuitry on the circuit board regulates the current through the LEDs and reduces the LED current under high temperature conditions.

Abstract: A dome structure has dimensions such as to house the cockpit of an aircraft. An ordered arrangement of light-emitting panels (10), able to be switched on or off selectively, forms at least a part of the inner vault of the dome. A floodlight (16) is mounted on a movable support arm (17) such that it can be selectively positioned around or above the cockpit and directed so as to project a beam of light onto the cockpit. Preferably a part of the inner vault of the dome consists of an ordered arrangement of reflective panels (11).

Abstract: The lighting apparatus, especially a reading lamp, has a light source (48), a movable cover (24) to which the light source (48) is fastened, an adjusting element (21) that cooperates with the cover (24), a bearing unit (26) for supporting the cover (24) and an adjusting ring (21). The cover (24) and light source (48) are movable around a longitudinal axis (L) of the lighting apparatus (10) by actuating the adjusting element (21) and the cover (24) and light source (48) are moveable around a transverse axis (Q) extending perpendicular to the longitudinal axis (L) by actuating the cover (24). The lighting apparatus in the form of the reading lamp is particularly useful aboard aircraft, ships, trains, automobiles, or other vehicles.

Abstract: An LED landing light arrangement for an aircraft comprises a plurality of LED light sources (12,14,16) for arrangement on an aircraft (24), primarily on the wing roots (20), on the front edges of the wings (22) and/or on the landing gears (18). The LED light sources (12,14,16) are operative to generate, relative to the central axis of the aircraft (24), a light distribution (10) ahead of the aircraft (24) that is spread substantially in a Y-shaped configuration in an obliquely downward direction. The light distribution (10) comprises two converging lateral regions (34,36) arranged laterally ahead of the aircraft (24), and a central region (40) running from said converging lateral regions (34,36) along an extension of said central axis and oriented in a direction away from the aircraft (24).

Abstract: The invention relates to a flush-mounted flashing light for approach guidance of aircraft, having a housing which has a housing pot (10) which can be inserted below ground level (F) and a housing cover (12) which covers this approximately at ground level (F) and having an optical system, which is arranged in the housing for controlled production and directed emission of light flashes, which comprises a light source (20) for production of light flashes and a prism (40) for varying the direction of the beam direction of the light flashes, with at least one light outlet opening (13) being provided in the housing cover (12) for light flashes to emerge from in a predetermined emission direction.

Abstract: The navigation lighting device for an aircraft, in particular a military aircraft and preferably a fighter aircraft is provided with several navigation light units with navigation lights, a power supply unit for the navigation tight units, and a central actuation unit for the actuation of the navigation light units in each one of several modes of operation. The navigation light units can be actuated for operation in a mode of operation by the central actuation unit sequentially in a predetermined sequence and thus with a time offset. Each navigation light unit comprises a control unit connected to the actuation unit for the actuation of its navigation light in the operation mode predetermined by the central actuation unit. The control units of the navigation light units comprise time-delay elements for the temporal delay of the actuation of the navigation lights on the receipt of an actuation signal of the central actuation unit.

Abstract: An aerially deployed illumination system is provided which may be remotely operated or preprogrammed to illuminate a designated target, such as a geographic area, vehicle, or personnel. In particular, a remotely controlled UAV having an illumination system disposed thereon is provided, the illumination system comprised of a concentrated light source and light movement apparatus operable to rapidly scan the target with the light source, thereby providing an illusion of a large area of illumination. Preferably, a line is created from the light source, the line being rapidly moved over the target in specific patterns and at specific frequencies. The system may further include a plurality of UAV's capable of ad hoc networking, so as to illuminate both large areas, as well as stationary and moving targets.

Abstract: Described is a novel aircraft lighting system with the potential for achieving increased efficiency, improved thermal management, higher reliability, and longer lifetimes. The proposed approach involves combining solar cells and light-emitting diodes (LEDs), and utilizing the cold temperatures of about ?50 degrees centigrade encountered in high-altitude (12,000 m) flight to improve thermal management and efficiency in both components.

Abstract: An aircraft light source includes a first substrate having an array of electromagnetic energy emitters connected in series and configured to radiate electromagnetic energy at one or more than one predetermined wavelength. The first substrate is configured to connect to a second substrate and is configured to electrically couple to the array of electromagnetic energy emitters to an aircraft electrical power system. The aircraft light source includes a housing having a cylindrical portion and a base portion. The cylindrical portion is configured to couple to a lens and to receive the array of electromagnetic energy emitters. The base portion is adapted and configured to electrically couple to an electric socket suitable for an incandescent filament lamp in an aircraft illumination system.

Abstract: An aircraft position light assembly having one or more light emitting diode (LED) modules. The LED module can be installed in a variety of aircraft wing-tip cavities. An example LED module includes a support device that mounts within an aircraft wingtip, a bracket device that attaches to the support device, at least one circuit board that mounts to the bracket, and two pairs of LEDs. Each pair of LEDs is mounted on opposing major surfaces at a first end of the circuit board. A first pair of reflectors is attached to the circuit board adjacent to two of the LEDs on the opposing major surfaces. A second pair of reflectors is attached to the circuit board adjacent to the other two LEDs on the opposing major surfaces.

Abstract: This invention relates to aircraft light units, in particular aircraft light units used when landing and taxiing an aircraft. The invention provides an aircraft light unit comprising a first light source with a principal beam axis in a first direction and a second light source with a principal beam axis in a second direction, the second direction being different from the first direction. The first and second light sources are arranged such that they can combine to create a net light beam in a plurality of different directions by variation of the power supplied to the light sources.

Abstract: Systems and methods for anti-collision lights on a UAV. A method for passive anti-collision lights on a Micro-Aerial Vehicle (“MAV”) including determining a location of the MAV using a flight management computer configured to fly the MAV on a programmed path using data from a global positioning system and an inertial navigation system. The flight management system transmits light activation data and selectively activates at least one navigation light located on a visible surface of the MAV using the light activation data from the flight management computer.

Abstract: An apparatus for illuminating an underside of a fuselage of an aircraft, the apparatus comprising a housing mounted to an underside of the fuselage; and a light source disposed within the housing the housing being configured to direct light from the light source toward the underside of the fuselage in an aft direction. Also disclosed is an aircraft advertising arrangement, comprising light emanation means for causing light to emanate from an underside of an aircraft fuselage, the light emanation means being configured to emanate light as a graphical advertising image.

Abstract: A reading device, such as a reading lamp or reading spotlight, is provided for use in a vehicle, such as a motor vehicle with immovable properties or ships. The reading device for example can be used in passenger cabins and/or cockpits of aircraft. The reading device includes, but is not limited to an LED light source with a color temperature that can be adjusted with the color “warm-white” to “cold-white”, a primary optics or lens advantageously designed as a converging lens, and a secondary optics or lens to focus the light emitted by the light source onto a surface, such as a reading plane to be illuminated.

Abstract: An aircraft external lighting system and method is applicable to aircraft position, navigation and strobe lights. The lighting system includes a light source, a cylindrical lens adjacent the light source, and a lenticular lens between the light source and the cylindrical lens.

Abstract: Light generated at a specific wavelength corresponding to a particular color or color range that is distracting or disruptive to a driver during a normal operation is blocked through an inexpensive construction without blocking light in a required range of wavelengths. A projector is constructed such that a plurality of LEDs are arranged in an array configuration. The LEDs can include a tinge of red reduction LED and near-infrared LEDs. The projector can be installed in a vehicle and disposed in proximity to the camera. In some embodiments, the projector can be controlled by a control circuit to be turned on in conjunction with the shutter of a camera.

Abstract: A position light including a base that is configured to attach to an aircraft. The base having an extruded overlap baffle. A first LED is coupled to the base underneath the overlap baffle. A circuit card is also coupled to the base and is extended over the first LED toward the over flap baffle. A second LED coupled to a circuit card. The extended overlap baffle and the extended circuit card block visible light emitting from the first LED.

Abstract: An aircraft cabin panel includes an aircraft cabin lighting seamlessly integrated with the panel. The aircraft cabin lighting includes at least one light emitting diode or LED and a diffuser. The diffuser includes a first body with a first index of refraction and a plurality of second bodies which are arranged in the first body and having a second index of refraction.

Abstract: An anti-collision light for aircraft comprising two illuminating modules each comprising a number of LEDs disposed along a ring and coplanar to a plane, a first reflector facing the LEDS and a second reflector surrounding the LEDS; the first and the second reflector are so configured as to reflect the light emitted by LEDs toward angles between 0 and 75° above or below said plane. An additional module providing infra-red radiation is may be provided; the additional module comprising number of infra red LEDs disposed along a ring and coplanar to a plane and a reflector facing the infra red LEDs.

Abstract: An aircraft navigation light comprises a base and circuit board in thermal contact with the base. White and colored LEDs mount on the circuit board. A reflector-shade placed adjacent the LEDs reflects light from the LEDs in desired directions and shades other directions from view of selected LEDs. A light transmissive cover sealed to the base, encloses the circuit board, LEDs and reflector-shade. Temperature responsive circuitry on the circuit board regulates the current through the LEDs and reduces the LED current under high temperature conditions.

Abstract: An individual cabin illumination device in an aircraft, the device having a light source associated with a passenger or with a group of passengers and an antidazzle device, wherein the antidazzle device includes a multitude of light-directing units which may be arranged one beside the other. Each light-directing unit includes a light-inlet aperture, a light-outlet aperture and a wall that connects the light-inlet aperture to the light-outlet aperture, wherein the light-directing units allow diffusion of the light that can be given off by the light source essentially only onto the passengers associated with the light source.

Abstract: An anti-collision light for an aircraft with a first light emitting level and a second light emitting level, wherein the first light emitting level is arranged above the second light emitting level and each light emitting level comprises a board on which light emitting diodes are arranged and a reflector for reflecting light emitted by the light emitting diodes essentially perpendicular to the board in a lateral direction, and wherein on the board of the first light emitting level the light emitting diodes are arranged on at least one straight line and on the board of the second light emitting level the light emitting diodes are arranged on a closed line that essentially has the shape of an ellipse or a rounded rectangle.

Abstract: A vehicle including a body having an exterior surface and a protrusion extending outward from the surface. The vehicle further includes a fairing mounted on the surface directly adjacent and behind the protrusion. The fairing has a forward end, an aft end opposite the forward end, and opposing sides extending between the forward end and the aft end. The opposing sides become progressively closer together from the forward end to the aft end so that the bracket has a tapered shape.

Abstract: An aircraft light source includes a first substrate having an array of electromagnetic energy emitters connected in series and configured to radiate electromagnetic energy at one or more than one predetermined wavelength. The first substrate is configured to connect to a second substrate and is configured to electrically couple to the array of electromagnetic energy emitters to an aircraft electrical power system. The aircraft light source includes a housing having a cylindrical portion and a base portion. The cylindrical portion is configured to couple to a lens and to receive the array of electromagnetic energy emitters. The base portion is adapted and configured to electrically couple to an electric socket suitable for an incandescent filament lamp in an aircraft illumination system.

Abstract: The invention relates to an electroluminescence (EL) element based on a particular zinc sulfide thick film with at least two planar electrodes, wherein at least one planar electrode is designed to be transparent. At least two AC voltage inputs are provided on each electrode at two points which are spaced apart. Moreover, the invention relates to methods for the production of the electroluminescence element and to the use thereof.

Abstract: There is provided a reading lamp having a lighting unit (BE) which has at least first light emitting diodes (LEDs) and/or second light emitting diodes (IR-LEDs) for the emission of IR radiation. The reading lamp further has a modulation unit (ME) for modulation of the light emission of the first and/or second light emitting diodes in dependence on an input signal (IN).

Abstract: An escape route marking for a passenger cabin in an aeroplane, with a plurality of longitudinal segments which are sequentially arranged along the escape route that is to be marked, wherein each segment has a support module and a light module that is arranged on the support module, and the light module has an essentially transparent plastic material into which photo-luminescent pigments are mixed which afterglow in the dark, wherein the pigments are micro-encapsulated in a second material such that liquid and moisture do not come into contact with the pigments.

Abstract: Escape path marking for an aircraft having a plurality of photoluminescent elements glow in the dark and of which each has a carrier element that is provided for attaching to a subsurface, characterised in that the carrier element has connecting edges on one or both end sides, the edges having an arc-shaped progression or having at least two sections not extending perpendicular to an orientation axis of the carrier element disposed perpendicularly on a cross section in the region of the connecting edge, the orientation axes of two carrier elements disposed successively enclosing an angle with each other.

Abstract: In certain embodiments, architectural lighting comprises a luminaire with a light source and a waveguide having forward and rearward surfaces. The waveguide can be disposed with respect to the light source such that light from the light source is input into the waveguide and guided therein. The waveguide can include a plurality of turning features that turn the light guided within the waveguide out the forward surface and one or more mounting fixtures for mounting the luminaire on an architectural structure. Some embodiments include a luminaire comprising a light source, a waveguide, turning features, and a lamp stand. Other embodiments are also described.

Abstract: Escape path marking for aircraft, which has an afterglowing photoluminescing material which is placed in several elements on the floor, characterised in that at least one element has a bent shape.

Abstract: The present invention relates to a flat discharge lamp (1000) that transmits in the visible and/or UV comprising first and second dielectric walls (2, 3) that are facing each other, kept parallel and sealed at the periphery (8), that thus define an internal space (10) filled with a plasma gas and comprising a source of UV and/or visible light (6); and first and second electrodes (4, 5) in separate planes parallel to the first and second walls, the first electrode (4) being at a potential V0 higher than the potential V1 of the second electrode, and the first electrode being arranged in the internal space and closer to the first dielectric wall than the second electrode.