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: An aircraft navigation light includes: a navigation lighting arrangement, having: a power input, couple able to an aircraft on-board power supply network, at least one navigation light source, and a power conditioning circuit, coupled between the power input and the at least one navigation light source for conditioning a power flow from the power input to the at least one navigation light source; an auxiliary power supply, coupled to the power conditioning circuit for diverting power from the navigation lighting arrangement; and a power supply output, coupled to the auxiliary power supply, for supplying power from the auxiliary power supply to an exterior aircraft light, external to the aircraft navigation light.

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: Described herein are systems, methods, and devices for recovering unmanned aerial vehicles (UAVs), such as UAVs that are trapped in an obstacle such as a tree. In particular, a method is described, the method including determining location parameters associated with a trapped UAV; navigating to the proximity of the UAV; determining launching parameters and a target associated with the launch of a launching device; and causing the launch of a launching device towards the target. The launching device may include a tether, such that a user may pull on the tether to dislodge the trapped UAV from the tree.

Abstract: A highly reliable flexible light-emitting device is provided. The light-emitting device includes a first flexible substrate, a second flexible substrate, a light-emitting element between the first flexible substrate and the second flexible substrate, a first bonding layer; and a second bonding layer in a frame shape surrounding the first bonding layer. The first bonding layer and the second bonding layer are between the second flexible substrate and the light-emitting element. The light-emitting element includes layer containing a light-emitting organic compound between the pair of electrodes. The second bonding layer has a higher gas barrier property than the first bonding layer.

Abstract: Provided is a beacon illumination device for signaling the presence of a wind turbine to aircraft, including an illuminator device having at least one light-emitting diode, at least one beacon light that can be mounted on an end part of the wind turbine at a distance from the illuminator device, at least one light conductor having optical fibers for transmitting light from the illuminator device to the beacon light, with the optical fibers being grouped in at least one bundle of optical fibers, with the illuminator device also having an optical collimator with at least one collimator lens disposed between the light inlet of the optical fibers and the light-emitting diode, for converting scattered light emitted by the light-emitting diode into a parallel beam of light and transmitting same towards the light inlet of the optical fibers.

Abstract: Lighting system for an aircraft, comprising at least one optical acquisition device, at least one long-range headlight each comprising at least one light source (3a,3b), closed-loop control means (4), and a means (5) for controlling the light sources (3a,3b) as a function of the data received from the optical acquisition device and from a data network of the aircraft in such a manner that the lighting system produces at least one beam for adaptive illumination with respect to the flight and taxi phases of the aircraft so as to illuminate at least one predefined region of the space around the aircraft.

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 computer is programmed to deploy an aerial drone to fly within a specified distance of a first vehicle. The computer is programmed to detect a second vehicle and then activate an aerial drone light.

Abstract: A landing zone designation system is provided that includes a master and a slave landing strobes. A detector on an aircraft can detect master and slave optical signals, and a processor can be coupled to the detector to compute placement of the aircraft relative to the master and slave landing strobes. A method is provided for designating a landing zone for an aircraft. The method includes emitting first and second optical signals, where a determination is made whether the aircraft is to land at a first landing zone or a second landing zone depending on a difference between the first optical signal and the second optical signal. A distance to landing within the determined first landing zone or the second landing zone can also be determined.

Abstract: An aircraft light for a foldable wing tip of an aircraft includes a first lighting structure, including at least one first light source and a first optical system, with the at least one first light source and the first optical system in operation generating a first light output; a second lighting structure, including at least one second light source and a second optical system, with the at least one second light source and the second optical system in operation generating a second light output; wherein the first light output and the second light output are of the same color and wherein the first light output and the second light output are angled with respect to each other; and wherein the aircraft light is configured to control the at least one first light source and the at least one second light source depending on a wing tip orientation signal, which is indicative of an orientation of the foldable wing tip.

Abstract: Provided systems and methods for an aircraft lighting system (ALS) include a centralized blue generator that supplies blue light to a plurality (N) of passive light-heads distributed at various locations on the aircraft. A load profile for use of the N passive light-heads during all flight phases and operational phases is developed and uploaded into the system. Each of the passive light-heads is operationally coupled to the blue light generator via a respective light transmission element that is gated with a respective one of N light switches. A light generating control unit (LGCU) is coupled to the blue light generator, and controls the generation and actuation of blue light, in addition to controlling light switch positions, as a function of navigation data and the load profile. Each of the N passive light-heads comprises a respective light conversion element to convert the blue light into red, green, or white light.

Abstract: An apparatus includes a light source configured to emit light, a beam shaper configured to project the light to substantially surround the apparatus in a plane and onto an object in the plane, and a receiver configured to project the light reflected from the object in the plane to an image sensor. A distortion parameter of the receiver in conjunction with a difference between the emitted light and the reflected light detected at the image sensor is indicative of at least one of a direction or a distance of the apparatus relative to the object.

Abstract: A vehicle system includes a processor and a memory storing instructions executable by the processor, the instructions including receiving an alert signal, deploying a drone from a host vehicle in response to receiving the alert signal, and commanding the drone to follow the host vehicle and to present a perceptible alert.

Abstract: An aircraft beacon light for being mounted to an aircraft fuselage includes: a support structure, having a carrier, and a stem for supporting the carrier and for spacing the carrier from the aircraft fuselage; and a lighting system, supported by the support structure, the lighting system having a plurality of light sources, light optics for redirecting at least a portion of the light emitted by the plurality of light sources, and a lens cover, with the plurality of light sources and the light optics being arranged between the carrier and the lens cover; wherein the aircraft beacon light is configured to emit a red-flashing beacon light output in operation.

Abstract: An aircraft lamp includes: a lamp outer case constituted by a lamp housing having an opening and a cover mounted to the lamp housing in a state where the opening is closed, an internal space being formed in the lamp outer case as an arrangement space; a light source including a light emitting diode and arranged on an arrangement surface inclined with respect to a predetermined surface to be irradiated in the arrangement space; and an inner lens arranged in the arrangement space and including a control lens configured to control an irradiation direction of light emitted from the light source. The control lens is formed in a shape having a longitudinal direction and a width direction, and the longitudinal direction and the width direction of the control lens are rotated in a direction around a light source optical axis with respect to a vertical direction and a left-right direction.

Abstract: A multi-mode aircraft navigation light includes a first light source of a first color; a second light source of a second color; and a common optical system, which is arranged over the first light source and the second light source for conditioning light emitted by either one of the first light source and the second light source; and a switching circuit configured to effect power supply to a selected one of the first light source and the second light source depending on a color selection signal.

Abstract: An aircraft wing assembly including a wing having a main body 5 and a movable portion 6, so that the wing may be folded when taxiing. A lighting system is provided with a light source 9; a light emitter 11 arranged on one of the main body and the movable portion, and a light guide 10 arranged to transmit light from the light source along a path between the main body and the movable portion to the light emitter. The provision of a light guide between the light source and the emitter allows for light to be transmitted to the emitter across the joint 8 between the wing main body and the movable portion. Thus, lighting on the wing may be provided without the need to provide electrical wiring across the joint. A single light source 9 may be employed to illuminate multiple light emitters 11, 13 on the wing.

Abstract: A rail vehicle lighting device includes: a plurality of short lighting fixtures assembled into a long lighting fixture having a shape matching with a shape of an irregular interior decoration. Each of the short lighting fixtures is provided with a section body. A light source is provided on the section body. The section body is twisted such that included angles between each of the light sources and a horizontal plane are consistent. In the rail vehicle lighting device, the plurality of short lighting fixtures is assembled into the long lighting fixture having the shape matching with the shape of the irregular interior decoration, thereby satisfying a requirement on a shape of a lighting fixture. By arranging the twisted section body, respective points of the long lighting fixture have consistent light source illumination angles, thereby achieving a satisfactory illumination effect inside a carriage having an irregular interior decoration, and accordingly improving the appearance of the carriage.

Abstract: The present technology is a luminaire lens and housing system for mechanically fastening of a light strip to a luminaire housing via a lens body. The system can include a luminaire housing formed from extruded modular luminaire housing sections assembled together, a mounting bracket mountable to the housing sections, and a lens body mountable to the mounting bracket. The mounting bracket includes a generally U-shape configuration capable of receiving the light strip and the lens body. The lens body can be a flexible polymeric lens of continuous length for the entire length of the luminaire housing. An interior section of the lens body includes legs receivable in depressions defined in the mounting bracket for retention thereof. The lens body is configured to contact and apply mechanical pressure to the light strip thereby securing the light strip in the mounting bracket or in the luminaire housing.

Abstract: A lens structure for placement over a light source and for attachment to a circuit board around the light source includes a circuit board engagement portion for being placed towards the circuit board, a recess provided in the circuit board engagement portion for receiving the light source upon attachment of the lens structure to the circuit board, a light entry surface around the recess, a lens body, a light exit surface distal from the circuit board engagement portion, and an attachment structure, the attachment structure being partially molded into the lens body and partially extending from the lens body for attaching the lens structure to the circuit board.

Abstract: An aircraft winglet light assembly is disclosed. The aircraft winglet light assembly includes an exterior skin coupled to an aircraft winglet of an aircraft. At least one interior surface of the exterior skin defines a cavity within the exterior skin. The aircraft winglet light assembly further includes one or more illumination sources housed within the cavity. The aircraft winglet light assembly further includes one or more sets of holes within the exterior skin. The one or more sets of holes are configured to allow illumination generated by the one or more illumination sources to pass through the exterior skin. The aircraft winglet light assembly further includes one or more protection elements proximate to the one or more sets of holes.

Abstract: An aircraft vertical stabilizer illumination light, configured to illuminate a vertical stabilizer of an aircraft, has a housing having a length (L), a width (W), and a height (H), the length (L) being greater than the width (W) and the height (H); and a plurality of light sources being arranged spaced along the length (L) of the housing (8) for a distributed illumination of the vertical stabilizer, wherein the housing (8) is configured to be mounted adjacent the vertical stabilizer on a tail portion of a fuselage of the aircraft.

Abstract: The present invention relates to a lighting means comprising at least two LEDs, mounted on opposite sides of a flat printed circuit board, said printed circuit board being combined with a reflector which is free of LEDs, a part of the light emitted by each LED being reflected by the reflector to homogenize the light distribution generated by the lighting means, and specifically in each case with a directional component parallel to a surface direction of the flat printed circuit board.

Abstract: A highly reliable flexible light-emitting device is provided. The light-emitting device includes a first flexible substrate, a second flexible substrate, a light-emitting element between the first flexible substrate and the second flexible substrate, a first bonding layer; and a second bonding layer in a frame shape surrounding the first bonding layer. The first bonding layer and the second bonding layer are between the second flexible substrate and the light-emitting element. The light-emitting element includes layer containing a light-emitting organic compound between the pair of electrodes. The second bonding layer has a higher gas barrier property than the first bonding layer.

Abstract: A luminaire system is provided that has directional light projection optics combined with a light distribution modifier to produce a non-uniform angular light intensity distribution from a single or array of light sources. The luminaire system provides for light intensity distribution with directional asymmetry meeting the specifications and requirements of aviation obstruction lights. The light distribution modifier component or subassembly redirects, scatters, refracts, diffracts and/or blocks part of the projection light in the distribution of the primary optics that would otherwise produce ground scatter. Unlike peripheral light shields at the marginal limits of the light distribution from the luminaire light system, the light distribution modifier is located near to the optical axis of the projection optics system.

Abstract: An exterior aircraft light unit includes a housing; a mounting structure, mounted to the housing and extending away from the housing substantially along a first cross-sectional plane; a lens cover, mounted to the housing, surrounding the mounting structure, and defining an inner space of the exterior aircraft light unit, with the mounting structure dividing the inner space of the exterior aircraft light unit into a first partial inner space and a second partial inner space; a plurality of anti-collision light sources, configured to emit respective sequences of warning light flashes in operation.

Abstract: A combined aircraft take-off and tower signal light unit comprises a mounting portion for mounting the combined aircraft take-off and tower signal light unit to an aircraft, wherein the mounting portion is configured for orienting a horizontal cross-sectional plane (H) of the combined aircraft take-off and tower signal light unit substantially horizontally with respect to the aircraft; and at least one light source. The combined aircraft take-off and tower signal light unit has a take-off light output, which is centered on a take-off light emission axis and which has a take-off light peak intensity, and a tower signal light output, which is centered on a tower light emission axis (B) and which has a tower light peak intensity.

Abstract: A signaling apparatus for command and/or indicating devices includes a base unit having at least two light sources which each generate light and are arranged on the base unit at a spacing from one another, and at least two light modules which are stacked along a main axis of the signaling apparatus and are operatively connected to the light sources such that light generated by the light sources is coupled into the light modules in a beam direction parallel to the main axis, the light modules each having a reflection region for reflecting at least in part the light coupled into the light modules in a signaling direction. A particular reflection region occupies only a portion of the light module in a peripheral direction of the corresponding light module perpendicular to the main axis of the signaling apparatus, which portion is smaller than a total periphery of the light module.

Abstract: There is provided a light-emitting device that makes is possible to emit light having less luminance unevenness.

Abstract: An aircraft light unit includes a mounting portion, which is configured for mounting the light unit to an aircraft; and at least one light source, which is configured for emitting light. The light unit is configured to emit at least one first output of white light into a predefined first spatial sector and to emit at least one second output of white light into a predefined second spatial sector. The light of the at least one first output of white light comprises a first percentage of radiation having a wavelength that is shorter than a predefined threshold, and the light of the at least one second output of white light comprises a second percentage of radiation having a wavelength that is shorter than the predefined threshold, wherein the first percentage of radiation is smaller than the second percentage of radiation.

Abstract: A method of operating an aircraft headlight system of an aircraft, the aircraft headlight system having at least one headlight, includes the steps of operating the aircraft headlight system in a landing light mode during a descent of the aircraft, with the at least one headlight emitting a landing light output in the landing light mode; operating the aircraft headlight system in a taxi light mode during taxiing of the aircraft, with the at least one headlight emitting a taxi light output in the taxi light mode; and transforming the landing light output into the taxi light output after touch-down of the aircraft by operating the aircraft headlight system in at least one intermediate lighting mode between operating the aircraft headlight system in the landing light mode and operating the aircraft headlight system in the taxi light mode.

Abstract: A light source includes a circular light element having a light source diameter, and a reflector disposed at least partially within the circular light element, the reflector having a first end with a first diameter and a second end with a second diameter, wherein the first diameter is less than the light source diameter and the second diameter is larger than the light source diameter, the second end having a plurality of slits.

Abstract: Embedded lighting, microphone, and speaker features for composite panels are described. An example composite panel includes a plurality of plies assembled in a stack-up, and a trace sheet with electrically conductive traces and a plurality of transducer discs positioned onto the electrically conductive traces at positions such that the electrically conductive traces form an electrical interconnection between selected ones of the electrically conductive traces and associated ones of the transducer discs. The trace sheet is included as an internal ply in the stack-up of the plurality of plies. The composite panel also includes a composite base upon which the stack-up of the plurality of plies is applied, and the plurality of plies are cured upon the composite base to integrate the trace sheet and the plurality of transducer discs into the composite base.

Abstract: A helicopter search light comprises a lighting arrangement comprising at least one light source and having an adjustable light output; a light detector, which is configured for detecting light reflected by the ground and/or at least one item on the ground and for providing a detection signal which is correlated to an amount of light detected; and a control unit, coupled to the light detector for receiving the detection signal and to the at least on light source for controlling the adjustable light output of the lighting arrangement.

Abstract: A dynamic aircraft headlight, includes an LED group, having a plurality of LEDs, and an optical system, comprising at least one optical element, for shaping an output light intensity distribution from the light emitted by the LED group. The LED group and the optical system are stationary within the dynamic aircraft light unit, with each LED of the LED group has a set position with respect to the optical system and with a light output of each LED being affected differently by the optical system.

Abstract: A lighting arrangement for an aircraft includes a navigational lighting group disposed along at least a leading edge of a wing of the aircraft and a light bar for non-navigational purposes extending along at least a portion of the leading edge of the wing, adjacent to the navigational lighting group, the light bar being disposed outboard of the navigational lighting group, the light bar being configured to emit non-navigational light along a length thereof.

Abstract: A method for producing an escape route marking in a heatable and malleable support mold is described. The escape route marking has a transparent covering, a supporting element and a photoluminescent material. The method includes procuring the heatable and malleable support mold, inserting a supporting element into the support mold, arranging the photoluminescent material on the supporting element, arranging the transparent covering on the supporting element, heating and deforming the escape route marking in the support mold and solidifying the escape route marking in the support mold in a predetermined position. The resulting escape route marking is also described.

Abstract: A lighting arrangement for an aircraft includes a navigational lighting group disposed at a leading edge of a wing of the aircraft. The navigational lighting group includes at least one right of way light. The lighting arrangement also includes a light bar extending along at least a portion of the leading edge of the wing, adjacent to the navigational lighting group. The light bar is configured to emit light along a length thereof.

Abstract: A dual-color aviation Anti Collision Light (ACL) has a first set of LEDs that emit a substantially white beam of light and a second set of LEDs that emit a substantially red beam of light. The ACL can be operated in a first mode in which the red LEDs are excited by themselves so that the ACL produces a red beam of light In a second mode, the white LEDs and the red LEDs are excited simultaneously to produce a white beam of light having a chromaticity within the definition of Aviation White. Operating the red LEDs in the white mode has two synergistic effects. First, the red LEDs augment the luminous output of the white LEDs so that fewer white LEDs are required, thus saving cost and space. Second, the red LEDs shift the chromaticity of total light output toward the red region. This has the effect of compensating for the tendency of the white LEDs to become greener with age.

Abstract: A headlamp (1) that utilizes a laser beam includes a scattered-light emitting unit (21) that emits scattered light upon receipt of a laser beam deviated from a predetermined path through which the laser beam is to pass or a predetermined irradiation region that is to be irradiated by the laser beam.

Abstract: A beacon light optic, comprising a reflective surface having an optical axis wherein the reflective surface is composed of surface parts of at least two at least partly overlapping at least segments of rotation symmetrical surfaces, an entrance area comprising an entrance surface for allowing light to enter the beacon light optic, an exit area through which light exits the beacon light optic, a light emitting element disposed in front of the entrance surface such that light emitting from the light emitting element enters the beacon light optic through the entrance area.

Abstract: A wing tip device has a lighting device arranged to project from a spanwise portion onto a substantially vertical portion of the wing tip device.

Abstract: A wingtip fin of an aircraft comprising an upstanding fin body, the fin body having an inboard face and an outboard face, a sign assembly in the fin body, the assembly comprising a translucent, graphic bearing face, substantially flush with and forming at least part of the inboard face or the outboard face of the fin body, a recess in the fin body behind the graphic-bearing face, and a light source arranged in the recess to illuminate the graphic-bearing face from inside the fin body.

Abstract: A lighting arrangement for an aircraft includes a navigational lighting group disposed at a leading edge of a wing of the aircraft. The navigational lighting group includes at least one right of way light. The lighting arrangement also includes a light bar extending along at least a portion of the leading edge of the wing, adjacent to the navigational lighting group. The light bar is configured to emit light along a length thereof.

Abstract: A strobe light includes a base, a mounting post, a plurality of light emitting diode (LED) lights, a control system, and a lens. The mounting post extends vertically from the base. The plurality of LED lights are mounted around a periphery of the mounting post. The control system is coupled to the plurality of LED lights and operable to independently control each LED light to produce at least one of a 360° strobe light pattern and a rotating beacon light pattern. The lens is connected to the base and covers the plurality of LED lights.

Abstract: The invention relates to a reading lamp for installation in a cabin trim element (4) of a vehicle, in particular of an aircraft, comprising an installation frame (1) having a ring element (2), a lamp housing (7) having a mating support surface (8), and a clamping ring (9) wherein the clamping ring (9) is connected to the installation frame (1) by means of tension spring elements (10), such that the lamp housing (7) is forced against the support surface (6) of the inner surface of the ring element (2) by means of the clamping ring (9) and may be moved with respect to the installation frame (1) in the manner of a ball and socket joint.

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 exterior aircraft light unit for emitting light of a first wavelength and light of a second wavelength, different from the first wavelength is disclosed. The exterior aircraft light unit has an integrated optical structure, which in turn has a first light source configured to emit the light of the first wavelength, a second light source configured to emit the light of the second wavelength, the second light source being positioned adjacent to the first light source, and an optical element for shaping a light emission distribution of the integrated optical structure. The optical element is arranged with respect to the first light source and the second light source in such a way that it affects both the light of the first wavelength and the light of the second wavelength.

Abstract: A method for controlling an aircraft having a plurality of LEDs, light so as to emit a desired light intensity includes the steps of providing a reference LED located within or outside of the aircraft light, providing thermal conditions resulting in a thermal stress for the reference LED similar to the maximum thermal stress, and observing the reference LED by means of an optical sensor for monitoring the optical aging behavior of the reference LED throughout its lifetime. The desired light intensity of the aircraft light is achieved by controlling the plurality of LEDs in accordance with the monitored aging behavior of the reference LED.