Abstract: A combined wing scan and winglet illumination light unit is disclosed. The light unit has at least one LED and at least one optical structure for shaping a light emission distribution of the combined wing scan and winglet illumination light unit. The wherein the light emission distribution has a first illumination region for illuminating a wing and a wing engine of an aircraft and a second illumination region for illuminating a wing tip winglet of the aircraft.

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: 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: An aircraft LED light unit is disclosed that includes a flat electric circuit device having a first main surface, a second main surface and at least one side surface extending between the first main surface and the second main surface, power supply circuitry, disposed in the electric circuit device, at least one heat transport element, disposed in the electric circuit device, and at least one LED. The at least one LED is arranged on the at least one side surface of the electric circuit device, is electrically coupled to the power supply circuitry, and is in heat exchange relationship with the at least one heat transport element.

Abstract: An exterior helicopter light unit is disclosed that comprises a movable light head comprising a light source, a first motor and a second motor for actuating the movable light head, and an inverse differential gear assembly coupling the first and second motors to the movable light head in such a way that the first and second motors can tilt and rotate the movable light head in operation.

Abstract: An exterior aircraft light unit for emitting light of a first wavelength and light of a second wavelength, different from the first wavelength, with corresponding emission characteristics is disclosed. The exterior aircraft light unit has at least one first light source configured to emit the light of the first wavelength, at least one second light source configured to emit the light of the second wavelength, and a wavelength selective optical element, which wavelength selective optical element is reflective for the light of the first wavelength and transparent for the light of the second wavelength.

Abstract: An aircraft galley, according to one implementation, includes a lighting system having a DC, linear LED task light that is positioned in a groove along the edge of an overhang above the galley's work surface. The task light is oriented downward orthogonally to the cabin floor so as to illuminate a work surface of the galley. In some implementations, the task light is angled so that it illuminates the work surface of the galley in which it is installed, the forward, aft, or cross-aisle opposing galley, if applicable, and the floor.

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 flat light for aircraft cabins is provided. The flat light has a light box and a light source, the light of which is coupled into the light box. A rear wall of the light box is formed to be reflective and the front wall of the light box has optical elements for directional emission of light.

Abstract: A method of providing synchronous control for a number of light-emitting diode (LED) units within a LED fixture is described herein. The method can include receiving an input signal. The method can also include sending, in response to receiving the input signal and for a period of time, a power-on delay signal to the LED units, wherein each LED unit includes a counter, a toggle, and a LED driver, where the power-on delay signal resets the counter, initializes the toggle, and disables the LED driver. The method can also include terminating, after the period of time, the power-on delay signal. A LED fixture and a LED unit within a fixture, having one or more components performing the aforementioned method, is also described herein.

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 PSU pod assembly that is configured to be positioned in the interior of an aircraft. The PSU pod assembly includes a PSU pod that includes a housing that includes a top, a bottom and first, second, third and fourth sides that cooperate to define a pod interior and a panel positioned above and connected to the PSU pod. The PSU pod includes at least first and second reading lights positioned within the pod interior that are configured to shine light below the housing and cabin lights positioned on or in the housing that are configured to shine light above the housing. The panel includes connectors that are configured to secure the PSU pod assembly to a component within the aircraft.

Abstract: A model airplane illumination system is disclosed. The system includes a plurality of carbon fiber wingtip rods, a wingtip mount configured to secure at least one of the wingtip rods substantially perpendicular to each wingtip of a model airplane, and a plurality of light emitting diodes (“LED”), where at least one LED of the plurality of LEDs is secured to each end of the wingtip rods and configured to illuminate surfaces of the model airplane. In addition, the system includes a carbon fiber tail rod, a tail mount configured to secure the tail rod to a tail of the airplane and configured to illuminate the surfaces of the airplane, and at least one LED of the plurality of LEDs is secured to each end of the tail rod and configured to illuminate the tail and fuselage surfaces of the model airplane.

Abstract: Described are lighting devices of passenger aircraft. Also described are methods of operating the devices as well as lighting systems and passenger service units.

Abstract: A strobe light unit, particularly wing anti-collision strobe light unit for an aircraft, comprises at least one light source, particularly at least one LED; a reflector element, the at least one light source and the reflector element being configured for projecting light into a desired range of directions; and a stray light blocking element for blocking stray light from being projected into undesired directions, the stray light blocking element attached to the reflector element or to a base portion of the strobe light unit.

Abstract: A method of selecting a lighting pattern of an aircraft is disclosed herein. The method comprises exposing a photoluminescent element to electromagnetic radiation emitted from a light source of the aircraft. The light source has (a) a spectral power distribution and (b) an illumination level. The method also comprises calculating a total energy absorbed by the photoluminescent element based on (a) the spectral power distribution, (b) the illumination level, and (c) an exposure duration. The method comprises correlating the total energy absorbed to a discharge duration based on a normalized photoluminescent response function of the photoluminescent element. And the method also comprises verifying that the (a) spectral power distribution, (b) illumination level, and (c) exposure duration of the light source are in compliance with operational guidelines for the light source and the photoluminescent element based on the discharge duration.

Abstract: An exterior structure component for an aircraft with an illuminating device includes a structure with an interior side and an exterior surface with at least one illuminated region and a multitude of optical fibers that extend from the interior side to the at least one illuminated region of the exterior surface. The optical fibers end on the interior side of the exterior structure component in a common interface area that is couplable to an illuminating device. The structure is made from a fiber composite material in which the optical fibers are integrated. In this manner a particularly weight-saving illuminating device that is capable of withstanding external influences may be provided.

Abstract: The present disclosure is directed to an automotive headlight. In one embodiment, the automotive headlight includes one or more first light emitting diodes (LEDs) and one or more second LEDs, wherein the one or more second LEDs are positioned at about 180 degrees with respect to the one or more first LEDs, wherein the headlight optical axis is about ?90 degrees with respect to a LED optical axis of the one or more first LEDs, at least one first reflector, wherein the at least one first reflector redirects light from the one or more first LEDs to an angle of about ?90 degrees with respect to a LED optical axis of the one or more first LEDs and at least one second reflector, wherein the at least one second reflector redirects light from the one or more second LEDs to an angle of about ?90 degrees with respect to the LED optical axis of the one or more first LEDs.

Abstract: An integrated aircraft landing and taxi light includes upper and lower reflector regions in the shape of substantially circular segments and a central longitudinal third reflector region extending between the upper and lower reflector regions. Landing light LEDs are arranged within the upper and lower reflector regions and the outer portions of the central longitudinal reflector region with the diagonals of the LED dies oriented substantially along radial lines extending outward from the center of the light. Taxi light LEDs are arranged within the central and outer portions of the central longitudinal reflector region such that the sides of the LED dies are oriented substantially horizontally and vertically with respect to the aircraft.

Abstract: Side emitting optical apparatuses and methods having an optical grade silicone component. Optionally, the optical grade silicone includes a plurality of diffusive side areas that are configured to disrupt the travel path of a light ray traversing along a longitudinal axis of the optical element to re-direct the light ray out of the side of the optical element. The optical apparatus is configured such that the light is emitted more uniformly along a length of the optical apparatus.

Abstract: A model airplane illumination system is disclosed. The system includes a plurality of carbon fiber wingtip conduits, a wingtip mount configured to secure at least one of the wingtip conduits substantially perpendicular to each wingtip of a model airplane, and a plurality of light emitting diodes (“LED”), where at least one LED of the plurality of LEDs is secured to each end of the wingtip conduit and configured to illuminate surfaces of the model airplane. In addition, the system includes a carbon fiber tail rod, a tail mount configured to secure the tail rod to a tail of the airplane and configured to illuminate the surfaces of the airplane, and at least one LED of the plurality of LEDs is secured to each end of the tail rod and configured to illuminate the tail and fuselage surfaces of the model airplane.

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: An aircraft light, particularly for emitting light onto a runway during takeoff or landing and/or onto the ground during taxi, comprises a light source (30), a reflector (12), a support frame (18) for the reflector (12), and an adjustable bearing arrangement (20) including at least two joints (22) pivotably supporting the reflector (12). The adjustable bearing arrangement (20) comprises at least one extendable and retractable adjustment element (24) guided at the support frame (18) along a movement axis (26). At least one of the two joints (22) is formed as a ball-type joint. The ball-type joint (22), to compensate for a change of the distance (A,A?) between the at least two joints (22) of the bearing arrangement (20) upon movement of the adjustment elements (24) for tilting the reflector (12), slidably engages the reflector substantially orthogonal to the movement axis (26) of the adjustment element.

Abstract: The present invention is directed to a high intensity light module for warning aircraft of obstructions. In one embodiment, the high intensity light module for warning aircraft of obstructions includes a first plate, at least one reflector coupled to the first plate along a length of the first plate, a plurality of light emitting diodes (LEDs) coupled to the first plate, wherein the at least one reflector redirects light emitted by the plurality of LEDs substantially along a single side of the high intensity light module, a lens coupled around a perimeter of the first plate and a second plate coupled to the lens around a perimeter of the second plate and coupled to the first plate via one or more standoffs.

Abstract: A lighting assembly that includes an outer housing defining an outer housing axis, an inner housing defining an inner housing axis and a light member positioned in the inner housing. The outer housing includes a front surface having a front opening and an inner surface that defines an adjustment cavity having a truncated spherical shape. The inner housing has a truncated spherical shape and is at least partially received within the adjustment cavity. The inner housing defines a light recess therein and includes a front cover having an aperture defined therein. The front cover at least partially defines the light recess. The light member defines a light axis. The light axis and the inner housing axis are not co-axial and not parallel and form an angle therebetween. The inner housing is adjustable between a home position and a plurality of adjustment positions.

Abstract: An anti-collision aircraft light comprises at least one LED and a control unit for operating the at least one LED in a pulsed manner. In this anti-collision aircraft light, the control unit comprises an ambient temperature sensor for sensing the ambient temperature and an adjustable current control for setting an LED operating current depending on the sensed ambient temperature. The control unit further includes a light intensity sensor for sensing the intensity of the light emitted from the at least one LED, an integrator connected to the light sensor for integrating the sensed light intensity, and a comparator for comparing the integrated light intensity to a threshold value. The operating current for the at least one LED is interrupted as soon as the integrated light intensity is equal to the threshold value.

Abstract: A service module for supplying passengers in a passenger space of a means of transport, in particular of an aircraft, and to a service system having a service channel and a plurality of such service modules. The service module comprises at least one service component arrangement having one or more service components for individually supplying one or more passengers, and a cabin lighting unit for illuminating the passenger space of the means of transport, in particular of the aircraft.

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 graphics display module that includes a frame with a front portion and a rear portion that cooperate to secure a hated panel having a front surface and a rear surface therebetween. The front portion defines a central opening through which the front surface of the lighted panel can be viewed, The front portion and rear portion cooperate to define a channel that includes lighting disposed therein that is configured to back light the lighted panel.

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: The present disclosure provides a directionally filtered indicator light, wherein a directional filter is applied to a light source that is controlled to emit light when a condition or series of conditions are met. The directional filter, in turn, regulates the transmission of light from the light source so that a first group of individuals, located within a viewing angle, are the only individuals able to see the transmitted light. In one example, the directionally filtered indicator light of the present disclosure allows an indicator light on the interior of a passenger aircraft to be viewed from outside the aircraft in direct sunlight while substantially eliminating the presence of transmitted light from a passenger seating area.

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: A system is for a landing site for a helicopter or a load suspended from a helicopter, where landing positioning references are visualized as a luminous pattern on the landing site, and where the landing positioning references are formed as lines of light projected on the landing site from one or more light sources arranged at the landing site. A method is for forming of landing positioning references visualized as a luminous pattern on the landing site.

Abstract: The warning lamp for an aircraft is provided with a housing (10) which possesses a light permeable cover (12) that is exposed to the surrounding air when the housing is mounted on the aircraft, with a frontal cover area and a rear cover area, a mounting element (44) to fasten the cover to a lower part (14) of the housing (10), wherein one edge (41) of the cover (12) is covered by an edge of the mounting element (44) and protrudes from it, a lamp with at least one LED (42,46,58,60), which is arranged within an area that is covered by the cover (12), and a cooling body (18) for the at least one LED (42,46,58,60), wherein the cooling body (18) possesses a cooling surface (32) that is exposed to the surrounding air when the housing (10) is mounted on the aircraft. The frontal cover area is formed by a frontal cover element (22) which is made from a light permeable first material. The rear cover area is formed by a rear cover element (28), which is made from a light permeable second material.

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: 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 passenger service system includes an individual ventilation arrangement and/or a lighting arrangement, wherein at least one air nozzle of the individual ventilation arrangement and/or at least one reading lamp of the lighting arrangement is/are disposed in the region of a service surface of the passenger service system, The service surface of the passenger service system includes a substantially flat portion as well as a buckled portion, which is curved convexly relative to the substantially flat portion and extends along a longitudinal axis (LP) of the passenger service system.

Abstract: An aircraft passenger suite including a seat configured for movement between an upright position and a horizontal bed position, an ottoman positioned apart from the passenger seat, and at least one armrest assembly configured for vertical movement, wherein the seat, ottoman and at least one armrest reside in horizontal alignment to form a bed in the horizontal bed position.

Abstract: Assemblies compliant with night vision imaging system (NVIS) standards are described. Versions of the assemblies incorporate filtering material into an encapsulant for a light-emitting diode (LED) die, avoiding any necessity of using external filtering agents. Alternatively or additionally, filtering material may be incorporated into a housing of an encapsulated LED.

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

Abstract: A rotorcraft (1) having on-board lighting equipment for lighting the surrounding environment. The lighting equipment comprises a plurality of headlights (2, 2?, 3, 3?) that are allocated to respective specific lighting functions in landing and in winching. The headlights (2, 2?, 3, 3?) are also operated to perform a searching lighting function. Control means determine which headlights (2, 2?, 3, 3?) are to be operated depending on a lighting function selected by an operator and depending on where the headlights are located on the rotorcraft (1). A search zone (4, 4?) for illuminating is identified by identification means on the basis of a lighting command common to the headlights (2, 2?, 3, 3?). Coordination means cause the headlights (2, 2?, 3, 3?) to converge on the identified search zone (4, 4?), while taking account of their respective locations on the rotorcraft (1).

Abstract: An aircraft cabin lighting kit includes: at least one lighting unit configured for installation in an aircraft cabin; a driving/dimming module generating output signals for controlling illumination of the at least one lighting unit according to command signals from a cabin management system; and at least one wire assembly interfacing the driving/dimming module with a power bus for receiving operational power, and a communication bus for receiving the command signals and for communicating the output signals to the at least one lighting unit. The present aircraft cabin lighting kit is certified by a governmental aviation-regulating body for installation in multiple aircraft.

Abstract: The present disclosure is directed to a light emitting diode (LED) signal light. In one embodiment, the LED signal light includes at least one visible LED, at least one infrared (IR) LED, a reflector, wherein the reflector collimates a light emitted from the at least one visible LED and a light emitted from the at least one IR LED and a power supply powering the at least one visible LED and the at least one IR LED.

Abstract: An integrated aircraft landing and taxi light includes upper and lower reflector regions in the shape of substantially circular segments and a central longitudinal third reflector region extending between the upper and lower reflector regions. Landing light LEDs are arranged within the upper and lower reflector regions and the outer portions of the central longitudinal reflector region with the diagonals of the LED dies oriented substantially along radial lines extending outward from the center of the light. Taxi light LEDs are arranged within the central and outer portions of the central longitudinal reflector region such that the sides of the LED dies are oriented substantially horizontally and vertically with respect to the aircraft.

Abstract: Methods for flying multiple aircraft in a predetermined formation in which a relative navigation grid is emitted from at least one of the aircraft, a spatial relationship is calculated based on the emitted relative navigation grid, and a relative position of at least one aircraft is altered to position the aircraft in the predetermined formation when the spatial relationship does not conform with the predetermined formation.

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 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: 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: A precision approach path indicator system (PAPI) including multiple LHA indicators and power sources. Each LHA indicator comprises several assembly modules, with each module made up of several red and white LEDs, several collimating lens, one optical combiner, and one projection lens set. From a side view of the module, the red LEDs are placed on top of white LEDs, with a collimating lens in front of each LED. The optical combiner is in front of both the red and white LEDs, slightly above the white LEDs in vertical placement. The optical combiner has a reflective coating on the bottom surface, and a red light filter coating on the projection surface. The combined beam of light is projected out through a projection lens at front of the assembly module.