Abstract: A balloon-mounted light source includes an array of LEDs mounted on, and cooled by, a balloon structure filled with a lightweight gas such as helium. The LEDs are preferably mounted in long series arrangements with small gauge wire to minimize weight. They may be mounted on heatsinks that are dispersed in a mesh-like structure over the balloon. The LED circuitry may also be mounted on flexible circuit boards, which may be porous to reduce weight. The balloon may include an envelope compartment with a leak-resistant seal or zipper to allow the interior of the envelope to be accessed, and a pressure relief valve. The envelope of the balloon may be clear in the front in order to maximize the projection of light but reflective along the back and sides as to minimize spill. The balloon may take the form of a controllable dirigible.

Abstract: Interior lighting and illumination systems for aircraft, particularly commercial passenger airplanes. Efficient beam forming optical light emitting diode arrangements having offset apertures for maximizing effectiveness are positioned in the ceiling panels above the aisles between sets of seats in the passenger cabins for cross bin illumination of stowage areas. The efficient beam forming optical LED devices are positioned to shine on opposite storage/stowage bins and are positioned to overcome line of height light source restrictions such as may be imposed by a valence. The devices are effective for illuminating across the aisles, thus creating a cross-bin lighting system.

Abstract: Compact illumination systems, particularly for aircraft, use efficient beam forming optical light emitting diode arrangements combined with beam turning and beam splitting prism optics and optional aspheric reflectors to direct light in a cross cabin or cross bin lighting application. The LED based compact illumination devices are positioned to shine on opposite storage/stowage bins without being directly visible to a passenger. The devices are effective for illuminating ceiling structures as well as across the aisles of a passenger cabin, thus creating a cross-bin lighting system.

Abstract: The incorporation of a variety of illumination sources to provide the additional light sources that reflect against a ceiling panel to provide an altered ceiling height effect in an aircraft. The incorporation of floor, aisle and door illumination provides the added benefit of facilitating emergency evacuation of the aircraft.

Abstract: An illumination device for an aircraft, comprising a combination of two-dimensional background illumination with a reflection of incident light on a face pointing towards the viewer in order to achieve a particular depth effect, as a result of which the illumination body appears to the viewer in greater visual depth than is actually the case. This is, in particular, of importance in aircraft, in which not only is the available space small, but also the weight aspect that is inevitably associated with large bodies plays an important role.

Abstract: A high intensity light is disclosed. A first circular lighting array having a plurality of reflectors and light emitting diodes is provided. A second circular lighting array is mounted on the first circular lighting array. The second circular lighting array has a second plurality of reflectors and light emitting diodes. Each reflector includes a tulip-shaped reflective surface having a symmetrical vertical cross section and a different symmetrical horizontal cross section. The reflective surface creates a uniform beam reflecting from a corresponding LED at horizontal angles relative to the reflective surface and a narrow beam in vertical angles relative to the reflective surface.

Abstract: A lighting assembly apparatus for wingtip position lights and an anti-collision light (ACL). The lighting assembly apparatus reduces light flashback caused by the ACL by including one or more internal baffles located inside of a lens. A lens retainer receives the lens. The lens retainer includes a base section and internal baffles. The one or more internal baffles include a crossbeam baffle that is attached between upper and lower surfaces of the lens retainer. The crossbeam baffle reduces light flashback caused by the ACL and complies with ACL/regulatory requirements. The internal baffle includes a stepped edge that also reduces light flashback caused by the ACL and complies with ACL requirements.

Abstract: Aircraft anti-collision light (ACL) systems and methods are operable to emit light from light emitting diode (LED) lamps. An exemplary embodiment includes a housing, a plurality of LED lamps within the housing and configured to emit light in a direction substantially perpendicular to the direction of light emitted from the ACL, and a reflector within the housing that is configured to reflect the light received from the plurality of LED lamps in the direction of light emitted from the ACL.

Abstract: An installation light for a vehicle or aircraft comprises a multitude of lighting elements. These lighting elements may be activated individually or in groups, in a manner such that the radiation direction and/or emittance angle of the light emitted by the installation light may be adjusted.

Abstract: An anti-collision light for large, commercial aircraft is disclosed. The light is a self-contained unit capable of easy replacement of any anti-collision light currently in use in any large aircraft using an adapter plate and adapter cable directly connected to 115 VAC 400 cycles from the aircraft. The light includes a plurality of round circuit boards with an annular ring of high intensity, surface mounted LEDs, with a disk having an edge configured as an offset half parabolic reflector made up of a plurality of conical facets. Angles of the conical facets are selected such that light from the LEDs is focused into a plurality of discrete planes from each facet, these planes concentrating the light into planar regions of discrete light intensity as required by the FAA. The disks with reflector edges also serve as heat sinks to dissipate heat developed by the LEDs.

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 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: A rotationally symmetrical anti-collision light (100, 200) for an aircraft utilizing light-emitting diodes (LEDs) is mounted to the fuselage of an aircraft. The LEDs (10, 10?, 20, 20?) may be configured in one or more concentric rings. The anti-collision light includes a reflector (30, 30?) configured to redirect the light emitted by at least one of the rings, so that the light pattern satisfies predetermined specifications.

Abstract: A lighting apparatus for a vehicle cab or cabin, having a plurality of reading lights for a plurality of passenger seats. A number of the reading lights is at least equal to the number of passenger seats, and a mean distance between the reading lights is less than a shortest possible distance between the passenger seats.

Abstract: An aircraft, in particular a helicopter, has light elements which are in the form of strips and are fitted to the edge of at least a number of windows. The light elements are provided with photoluminescent material.

Abstract: A compact aircraft external illumination lamp has a discharge bulb as a light source that ensures a waterproof property. The aircraft external illumination lamp includes a container-shaped reflector serving also as a lamp body, a front cover attached to a front opening of the reflector, and a discharge bulb inserted in a bulb insertion hole formed in the reflector. A power supply socket is attached to a back side of the reflector so as to cover a peripheral edge of the bulb insertion hole. The power supply socket thus longitudinally fits on a plug portion of the discharge bulb which projects rearward of the bulb insertion hole, whereby electric connection with the discharge bulb is ensured. The power supply socket is structured so that a bulb activation circuit is embedded therein and a socket main body having a plug-portion fitting hole formed on a front side thereof is covered with a resin mold layer.

Abstract: An aircraft emergency lighting system including: a plurality of units having communication devices arranged to communicate wirelessly with a master controller, wherein each unit is wired to a common power supply for powering the unit in a first mode of operation and has its own back-up battery power supply for powering the unit in a second mode of operation, and wherein the device is provided for off-load testing the back-up battery power supply of each unit and indicating if the unit is operational.

Abstract: A lighting fixture for providing illumination comprising a housing, a printed circuit board, and a plurality LEDs connected to the printed circuit board. Optionally an emergency LED may also be included. A heat sink is connected to the housing and printed circuit board. Each of the plurality of the LEDs is mounted on the heat sink. A reflector is disposed inside the housing such that the light from the LEDs is mixed together and projected out of the illumination end of the housing by the surface of the reflector. The lighting fixture is received into a mounting flange assembly. A method for providing illumination using the above.

Abstract: A retrofit HID lamp assembly adapted for use in a non-HID lighting receptacle includes in one embodiment: (1) a housing compatible in size and shape with the receptacle; (2) a ballast unit disposed substantially within the housing interior; (3) a base terminal structure receiving electrical inputs and communicatively coupled to the ballast unit; (4) an aperture-defining reflector disposed within the housing; a lens bounding a reflector cavity; and an HID lamp having a light emissive portion that is removably insertable through the reflector aperture into the reflector cavity, and having a base portion that is electrically coupleable with the ballast unit. Fabrication and retrofit method are further provided.

Abstract: A lighting assembly apparatus for wingtip position lights and an anti-collision light (ACL). The lighting assembly apparatus reduces light flashback caused by the ACL by including one or more internal baffles located inside of a lens. A lens retainer receives the lens. The lens retainer includes a base section and internal baffles. The one or more internal baffles include a crossbeam baffle that is attached between upper and lower surfaces of the lens retainer. The crossbeam baffle reduces light flashback caused by the ACL and complies with ACL/regulatory requirements. The internal baffle includes a stepped edge that also reduces light flashback caused by the ACL and complies with ACL requirements.

Abstract: An device, method, and aircraft are provided for illuminating an in-flight operation, the device, method, and aircraft generating an electromagnetic radiation within the far-violet and ultraviolet spectrum, and thus being imperceptible to the naked eye, compatible with night vision equipment, and undetectable by night vision equipment.

Abstract: An illumination system for an aircraft passenger cabin has a first illumination source positioned between a ceiling structure and a first row of stowage bins. A first light direction assembly is positioned between the ceiling structure and the first row of stowage bins. The first light direction assembly is used to direct emitted light from the first illumination source onto a face of a luggage bin of a second row of stowage bins. A second light direction assembly is also positioned between the ceiling structure and the first row of stowage bins and is used to direct emitted light from the first illumination source into a passenger cabin. A second illumination source is positioned between the ceiling structure and the first row of stowage bins to illuminate the ceiling structure.

Abstract: The invention relates to an aircraft window case (10) that can be artificially illuminated in an indirect manner, comprising a connecting cone (20) for connection of the aircraft window case (10) to the inner face of an aircraft window (22), a panel (12) closing off the window case (10) from the aircraft interior, a hollow-cylindrical transition element (18) made of translucent material for spanning a distance between the connecting cone (20) and the panel (12), and an illumination device (24) which radiates light on to the outer face of the transition element (18).

Abstract: A window unit for an aircraft with which individual lighting scenarios can be produced. In addition, an aircraft is equipped with at least one window unit. The window unit includes a window pane, which is coated with an electrically actuatable shading device for reducing incidental light entering through the window page. In addition, the window unit includes a control unit for operating the shading device as well as a lighting device for producing a light effect in the region of the window unit. In this connection, the control unit has an interface via which the control unit is connected to a network system of the aircraft for operation of the shading device. Likewise, the lighting device is coupled with the control unit, so that the lighting device can be operated with the network system of the aircraft via the interface of the control unit.

Abstract: An illumination system for an aircraft passenger cabin has a first illumination source positioned between a ceiling structure and a first row of stowage bins. A first light direction assembly is positioned between the ceiling structure and the first row of stowage bins. The first light direction assembly is used to direct emitted light from the first illumination source onto a face of a luggage bin of a second row of stowage bins. A second light direction assembly is also positioned between the ceiling structure and the first row of stowage bins and is used to direct emitted light from the first illumination source into a passenger cabin. A second illumination source is positioned between the ceiling structure and the first row of stowage bins to illuminate the ceiling structure.

Abstract: A lighthead for a dual-mode searchlight including a generally concave housing with an attached infrared (IR) light source assembly, an insulating barrier and air gap between the visible and IR portions of the assembly, and a reflector integral to the housing.

Abstract: A lighting panel capable of producing a “Starry Sky” lighting effect and which is easily retrofitted into existing aircraft includes a first substrate, a plurality of microminiature light sources, such as LEDs, mounted on an upper surface of the first substrate, a plurality of electrically conductive traces written on the upper surface of the first substrate so as to make electrical interconnections with respective leads of the light sources, a clear filler material surrounding each light source and tapering down to the upper surface of the first substrate so as to planarize it, and a flexible decorative film laminated over the upper surface of the first substrate and light sources, the decorative film containing a plurality of apertures therethrough, each corresponding in location to a respective light source.

Abstract: A lighting panel capable of producing a “Starry Sky” lighting effect and which is easily retrofitted into existing aircraft includes a structural panel, a plurality of inserts containing microminiature light sources, such as LEDs, mounted in openings in the panel, a plurality of electrically conductive traces written on the upper surface of the panel so as to make electrical interconnections with respective leads of the light sources, and a decorative film applied over a bottom surface of the panel and the light sources, the decorative film being translucent or transparent or containing a plurality of apertures therethrough, each corresponding in location to a respective one of the light sources.

Abstract: Interior lighting and illumination systems for aircraft, particularly commercial passenger airplanes. Opposing pairs of LED lamps are positioned in the ceiling panels above the aisles between sets of seats in the passenger cabins. One set of LED lights are directed to illuminate the ceiling panels and may be in a particular color. The other set of LED lights are positioned to shine their lights on storage/stowage bins positioned across the aisles, thus creating a cross-bin lighting system. This enhances the cabin architecture and provides cabin illumination. A reflector can be positioned to direct the light and reduce possible glare to the passengers. The reflector directs the light rays from the LED lights which emanate from the top of the reflector to shine on the lowest part of the bins. The light rays leaving the reflector cross in front of the reflector.

Abstract: The light for a vehicle, particularly a flash warning light for an aircraft, is provided with at least one LED (10) bearing a semiconductor chip (14) emitting electromagnetic radiation. The semiconductor chip (14) emits blue or UV light. A conversion material (18) is arranged in the beam path that is permeable to low-energy radiation portions of the emitted light and is partly permeable to high-energy radiation portions of the emitted light, wherein a part of the high-energy radiation portions of the emitted light can be converted into low-energy radiation portions by the conversion material (18) The part of the high-energy radiation of the emitted light that penetrates the conversion material (18) is limited by means of an optical element and can partly be used again to increase efficiency.

Abstract: Disclosed is an airport light base including a light base container having an upper end with an inverted first flange having a first outer face, an opposing first inner face facing into the light base container, a continuous inwardly directed first edge bounding a first opening into the light base container, and ring segments affixed to the inner face of the first flange forming an inverted second flange under the first opening outboard of the first edge, the second flange for reception of an inset light fixture thereon and having a second outer face facing the first opening, an opposing second inner face facing into the light base container, and a continuous inwardly directed second edge bounding a second opening into the light base container, wherein the second opening is smaller than the first opening.

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 dome light is disclosed which utilizes a rotating knob with ‘on’ and ‘off’ positions to toggle between having either a halogen bulb on or a plurality of red LEDs on, or both off. Dual D-type flip-flops toggle the dome light between states in response the changes of the knob between the ‘on’ and ‘off’ positions. The plurality of red LEDs utilize at least one current regulator to maintain a constant level of illumination. When the halogen bulb is on, further rotation of the knob varies a potentiometer which controls the duty cycle created by a pulse width modulator. The pulse width modulator causes the halogen bulb to be on for portions of each cycle; the longer the ‘on’ time during each cycle, the greater the apparent intensity of illumination by the halogen bulb.

Abstract: The incorporation of a variety of illumination sources to provide the additional light sources that reflect against a ceiling panel to provide an altered ceiling height effect in an aircraft. The incorporation of floor, aisle and door illumination provides the added benefit of facilitating emergency evacuation of the aircraft.

Abstract: An interior sidewall panel assembly for a passenger aircraft includes a generally planar sidewall structural panel having a D-shaped window opening with an apex that is directed rearward and tilted slightly upward relative to the horizontal, a window assembly disposed in the window opening, an indirect lighting module disposed at a forward edge of the D-shaped window assembly and arranged to direct light forwardly such that the light washes onto a rear margin of a structural panel of a next adjacent panel assembly located immediately forward of the light module, and a kick panel disposed at a lower margin of the structural panel that incorporates cabin ventilation or decompression ducts and vents and an accent light adapted to direct light onto a cabin floor of the aircraft.

Abstract: An aircraft rear position light device (1) has a modular configuration. The device utilizes solid-state light sources. In an exemplary embodiment, the light sources are side-emitting light-emitting diodes (LEDs) (40), which are attached to a heat sink (30). A reflector (200) is positioned next to each of the LEDs. The device further includes an outer lens (10) with an integrated cut-off shield (110) and optical treatments (120). The configuration of LEDs and reflectors, in conjunction with the cut-off shield and optical treatments, allows the emitted light to satisfy predetermined minimum and maximum angular intensity requirements. An electronics module (50) is also attached to the heat sink to connect the LEDs to a power source in the aircraft. Electronic updates may be made by replacing the electronics module.

Abstract: A rotorcraft, such a helicopter or a tiltrotor aircraft, includes a light emitting device configured to provide light at a tip of a rotor blade. The light emitting device includes a light emitting diode arranged on the rotor blade, and a power source, wherein the power source is configured to power the light emitting diode due to a movement of the rotor blade. The power source may include a piezo-electric material configured to create a voltage due to movements of the rotor blade or an electrical generator including a stationary magnet assembly and a moveable coil assembly arranged on a shaft that rotates the rotor blade.

Abstract: The present invention relates to an illumination strip by means of which a handrail recess that itself at the same time forms a handrail can be illuminated; to a hatrack for installation in an aircraft cabin with a correspondingly designed handrail recess that at least in sections can be illuminated; as well as to the use of an illumination strip or a hatrack in an aircraft. The illumination strip comprises carrier module for accommodating an illumination means and a multitude of illumination means that are accommodated by the carrier module. The carrier module is strip shaped and comprises at least one positive locking means by means of which, for the purpose of illuminating the handrail recess, the carrier module can be fitted into the handrail so as to provide a positive-locking fit and so as to be exchangeable.

Abstract: A programmable and alternately configurable lighting fixture including a light emitting diode array adapted to affixed within a fixture housing. The lighting fixture includes a controller that is adapted to selectively power the plurality of light emitting diodes to provide two or more light beam patterns, each of the two or more light beam patterns selectively directable to two or more distinct lighting areas. The controller and the plurality of light emitting diodes are conductively connected to a power supply. The controller is programmable such that the lighting fixture is adaptable to various seating and lighting configurations, for instance a two seat/two beam configuration, a three seat/three beam configuration or a four seat/four beam configuration. Interchangeable lens assemblies are configured to appropriately direct and focus the selected number of lighting beams to the selected and distinct lighting areas.

Abstract: A white anti-collision light mounted on an aircraft utilizes a set of high-power light-emitting diodes (LEDs) and dedicated reflectors to distribute the light in a particular pattern that satisfies predetermined intensity requirements along a horizontal coverage area. The anti-collision light may include heat pipes for transferring heat from the LEDs to a set of cooling fins. Also, the LEDs may be electrically connected and controlled to provide redundancy and mitigate the effects of LED failures.

Abstract: A method for generating visible light and a deceptive signature pattern for an emissions producing asset is disclosed. The method comprises illuminating at least one lighting assembly of the asset in a pattern. The pattern produces visible light synchronous with a signature of a wavelength in a substantially similar range as normal emissions of the asset. The method also comprises modulating a radiant intensity of the signature of the at least one lighting assembly between a minimum radiant intensity and a maximum radiant intensity in a repetitive cycle and operating a controller to regulate the pattern.

Abstract: The following is an aircraft warning light adjustment system. Levels of ambient light and/or reflected light can be detected by detectors and transmitted to a processing unit. A processing unit, based on the received detections, can make automatic decisions concerning whether to turn on or off automatic warning lights located on the aircraft. If the aircraft is flying at night in cloudy conditions, the warning lights can be automatically turned off before the reflections from the clouds can cause pilots to experience night blindness, vertigo, or other problems caused by the reflected light.

Abstract: Multi-mode exterior lighting architectures for aircraft are provided. In accordance with an exemplary embodiment, an illumination system for illuminating a plurality of positions exterior to an aircraft includes a first light assembly coupled to the aircraft. The first light assembly is configured to produce a first light beam and direct the first light beam at a first position during a first operational mode and at a second position during a second operational mode. A second light assembly also is coupled to the aircraft and is configured to produce a second light beam and direct the second light beam at a third position during the first operational mode and at a fourth position during the second operational mode.

Abstract: An emergency lighting arrangement preferably includes plural emergency light units connected to an on-board power supply network of an aircraft, and plural emergency current sources that each include at least one capacitor. Each emergency light unit includes an emergency light emitting element and a control unit that automatically connects the capacitor of the emergency current source to the emergency light emitting element upon the failure of the on-board power supply network. Preferably, the emergency current source including the capacitor is integrated into the emergency light unit. The emergency light unit may further include normal operation light emitting elements selectively connected by the control unit to the on-board power supply network. The control unit switches between normal operation of the normal light emitting elements and charging of the capacitor, and emergency operation in which the capacitor discharges through the emergency light emitting element.

Abstract: The invention relates to a device and method for displaying luminous radiation on a shell of an aircraft, comprising at least one light source for producing luminous radiation, and at least one projection device for converting the luminous radiation into projectable luminous radiation. The at least one projection device is mounted inside the shell in order to project the luminous radiation through the interior (15) and onto the shell (60). Said shell is translucent at least in portions thereof whereby making the projected luminous radiation visible from the outside. The invention also relates to a method for displaying luminous radiation on a shell of an aircraft.

Abstract: The invention relates to an aeroplane comprising several decks which are arranged above each other, for passengers, freight and/or crew members, also comprising at least one staircase connected to the decks. Said aeroplane is characterized in that the staircase is provided with photoluminescent markings which enable the staircase to be recognized easily, even in poor lighting conditions, whereby orientation of passengers and crew members to exit is made easier in the event of an emergency.

Abstract: An aircraft emergency lighting system including: a plurality of units having communication devices arranged to communicate wirelessly with a master controller, wherein each unit is wired to a common power supply for powering the unit in a first mode of operation and has its own back-up battery power supply for powering the unit in a second mode of operation, and wherein the device is provided for off-load testing the back-up battery power supply of each unit and indicating if the unit is operational.

Abstract: An installation light for a vehicle or aircraft comprises a multitude of lighting elements. These lighting elements may be activated individually or in groups, in a manner such that the radiation direction and/or emittance angle of the light emitted by the installation light may be adjusted.

Abstract: A first light-emitting unit (11a), a second light-emitting unit (11b), . . . are disposed near a tip vicinity of a spinner cover (1) of a propeller (2). The first light-emitting unit (11a) embraces a first bulk-shaped lens of bullet-like, and a semiconductor light-emitting element is installed in a cavity of the first bulk-shaped lens. The second light-emitting unit (11b) embraces a second bulk-shaped lens of bullet-like, and a semiconductor light-emitting element installed in a cavity of the second bulk-shaped lens. The first light-emitting unit (11a) and the second light-emitting unit (11b) are formed so as to be able to attach to and detach from the spinner cover (1) as an attachment (4) for bird strike protection.

Abstract: This invention provides a light emitting array apparatus for use in a video screen display or lighting device incorporating a panel having a plurality of LEDs. Such a panel provides a plurality of LEDs on the front face of the panel in close thermal proximity to the panel. Typically this would include LEDs mounted to a PCB that is then affixed to the panel such that heat may transfer from the LEDs into the support panel itself. The support panel can disperse the heat throughout the panel and the to the surrounding air, especially from the front face of the panel. Such a construction may alleviate the need for fans or other cooling apparatus behind the panel and allow for the panel to be fitted directly to a supporting wall or other structure and also reduce cost and bulk of construction.