An exterior aircraft light cover with integrated illumination includes a mounting portion, configured to be mounted to an exterior aircraft light housing; a light transmissive pane, supported by the mounting portion. The mounting portion and the light transmissive pane are configured to jointly close the exterior aircraft light housing. The cover also includes at least one photovoltaic device, which is configured for generating electric energy when illuminated; at least one electric storage device, which is configured for storing the electric energy generated by the at least one photovoltaic device; and at least one ancillary light source, which is operable with electric energy supplied by at least one of the at least one photovoltaic device and the at least one electric storage device.
F21S 9/03 - Lighting devices with a built-in power supplySystems employing lighting devices with a built-in power supply the power supply being a battery or accumulator rechargeable by exposure to light
F21V 23/00 - Arrangement of electric circuit elements in or on lighting devices
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
2.
Rotorcraft lighting equipment, rotorcraft comprising such equipment, and method of illuminating an environment of a rotorcraft
Rotorcraft lighting equipment includes a plurality of lighting devices configured to be mounted to an exterior of a rotorcraft, wherein each of the lighting devices comprises a plurality of individually controllable lighting modules which are configured for emitting light into different spatial directions; and a lighting control device configured for individually controlling the operation of the plurality of lighting modules for generating a desired light distribution of the light emitted by the plurality of lighting modules.
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
H05B 45/10 - Controlling the intensity of the light
F21S 2/00 - Systems of lighting devices, not provided for in main groups or , e.g. of modular construction
F21V 5/04 - Refractors for light sources of lens shape
F21Y 105/18 - Planar light sources comprising a two-dimensional array of point-like light-generating elements characterised by the overall shape of the two-dimensional array annularPlanar light sources comprising a two-dimensional array of point-like light-generating elements characterised by the overall shape of the two-dimensional array polygonal other than square or rectangular, e.g. for spotlights or for generating an axially symmetrical light beam
F21Y 105/16 - Planar light sources comprising a two-dimensional array of point-like light-generating elements characterised by the overall shape of the two-dimensional array square or rectangular, e.g. for light panels
A helicopter search light includes a movable light head comprising: at least one light source and at least one optical element, which are configured for emitting a search light beam; at least two radiation sensors arranged in a preset distance (d) from each other. The radiation sensors are configured for detecting electromagnetic radiation and providing corresponding sensor signals. The system also includes an image processing module configured for receiving the sensor signals provided by the at least two radiation sensors and generating enhanced image data from said sensor signals and a controller configured for controlling movement of the movable light head depending on said enhanced image data.
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
H04N 13/239 - Image signal generators using stereoscopic image cameras using two 2D image sensors having a relative position equal to or related to the interocular distance
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
F21V 14/02 - Controlling the distribution of the light emitted by adjustment of elements by movement of light sources
G06V 40/10 - Human or animal bodies, e.g. vehicle occupants or pedestriansBody parts, e.g. hands
4.
Navigation light system for an unmanned aerial vehicle, unmanned aerial vehicle, and method of operating a navigation light system of an unmanned aerial vehicle
A navigation light system for an unmanned aerial vehicle, such as a multicopter type unmanned aerial vehicle, includes: a plurality of light emission units. E of the plurality of light emission units has a unit-specific light emission direction and is configured to provide a light output around the unit-specific light emission direction. Each of the plurality of light emission units includes a multi-color light source capable of emitting red light, green light, and white light. The plurality of light emission units are arranged to jointly provide a navigation light pattern around the unmanned aerial vehicle and wherein the light outputs of adjacent light emission units have an overlap the navigation light system is configured to operate each of the plurality of light emission units depending on a relation between a momentary flight direction of the unmanned aerial vehicle and the respective unit-specific light emission direction.
An exterior helicopter light is configured to be mounted to a helicopter, in particular to an underside of the helicopter, the helicopter having a longitudinal axis (A). The exterior helicopter light comprises: a first set of light sources configured for emitting, in operation, light of a first color into a at least one rear sector of a ground below the helicopter, the at least one rear sector spatially extending around a projection of a rear portion of the helicopter onto the ground; and second set of light sources configured for emitting, in operation, light of a second color, which differs from the first color, into at least two forward sectors of the ground below the helicopter.
F21S 41/40 - Illuminating devices specially adapted for vehicle exteriors, e.g. headlamps characterised by screens, non-reflecting members, light-shielding members or fixed shades
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
F21Y 105/18 - Planar light sources comprising a two-dimensional array of point-like light-generating elements characterised by the overall shape of the two-dimensional array annularPlanar light sources comprising a two-dimensional array of point-like light-generating elements characterised by the overall shape of the two-dimensional array polygonal other than square or rectangular, e.g. for spotlights or for generating an axially symmetrical light beam
F21Y 113/13 - Combination of light sources of different colours comprising an assembly of point-like light sources
A cover for an exterior aircraft light includes a lens cover structure, attachable to an exterior aircraft light housing and configured to close the exterior aircraft light housing, wherein the lens cover structure has an inside and an outside and is at least partially made of transparent material; and a wear indicator, attached to the inside of the lens cover structure, the wear indicator having a contrasted pattern visible from the outside of the lens cover structure through the transparent material.
F21S 43/20 - Signalling devices specially adapted for vehicle exteriors, e.g. brake lamps, direction indicator lights or reversing lights characterised by refractors, transparent cover plates, light guides or filters
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
F21V 17/00 - Fastening of component parts of lighting devices, e.g. shades, globes, refractors, reflectors, filters, screens, grids or protective cages
7.
Replaceable light head for exterior aircraft light, and method of evaluating an operating status of an internal power supply of an exterior aircraft light
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.
F21V 17/00 - Fastening of component parts of lighting devices, e.g. shades, globes, refractors, reflectors, filters, screens, grids or protective cages
An illuminated aircraft passenger cabin gasper comprises an air outlet for outputting a flow of air into an aircraft passenger cabin and an air guide, movably arranged within the air outlet for adjusting the flow of air that includes a light guide. The gasper also includes at least one light source, arranged adjacent to the light guide for coupling light into the light guide. The light guide has a light output surface for coupling light out of the light guide into the aircraft passenger cabin.
F21V 33/00 - Structural combinations of lighting devices with other articles, not otherwise provided for
F24F 13/078 - Outlets for directing or distributing air into rooms or spaces, e.g. ceiling air diffuser combined with lighting fixtures
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
9.
Combined aircraft navigation and anti-collision light, and method of determining a state of erosion of a lens cover of a combined aircraft navigation and anti-collision light
A combined aircraft navigation and anti-collision light, includes: at least one navigation light source and one anti-collision light source; a navigation light sensor, in operation outputting a light detection signal corresponding to an amount of light detected by the navigation light sensor; first and second optical systems, associated with navigation and collision light sources, wherein the first optical system is configured for shaping a navigation light output from light emitted by the at least one navigation light source and is configured for directing stray light from the at least one navigation light source to the navigation light sensor and a second optical system, associated with the at least one anti-collision light source and configured for shaping an anti-collision light output from light emitted by the at least one anti-collision light source; a lens cover, arranged over the light sources and optical systems for passing light therethrough.
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
H05B 47/20 - Responsive to malfunctions or to light source lifeCircuit arrangements for operating light sources in general, i.e. where the type of light source is not relevant for protection
H05B 47/105 - Controlling the light source in response to determined parameters
F21S 10/06 - Lighting devices or systems producing a varying lighting effect flashing, e.g. with rotating reflector or light source
An aircraft passenger reading light include comprises: a light source arrangement having a plurality of rows of reading light sources, with each of the rows having a plurality of reading light sources for passenger-specific illumination of a plurality of seats of a seating row of an aircraft and with the plurality of rows having different illumination directions in a longitudinal direction (L) of the aircraft, whereinach of the light sources first and second electrical terminals; first and second power supply connectors; and a multi-state switching arrangement having a plurality of switching states. The first power supply connector is coupled to the first electrical terminals of the plurality of reading light sources. The second power supply connector is coupled to the second electrical terminals of the plurality of reading light sources via the multi-state switching arrangement.
B60Q 3/76 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors characterised by the purpose for spotlighting, e.g. reading lamps
An exterior aircraft image projector includes at least one light source, providing a light output in operation; an optical system configured for transforming the light output of the at least one light source into a light beam and projecting said light beam onto the ground below the aircraft and the of the aircraft; a photo detector arranged to detect a brightness level (Iambient) of the ground or the exterior and configured to provide a corresponding brightness signal; and a controller, coupled to the photo detector and the at least one light source configured to control an intensity of the light output of the at least one light source as a function of the brightness level (Iambient), as provided by the photo detector via the brightness signal.
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
G03B 21/14 - Projectors or projection-type viewersAccessories therefor Details
H04N 9/31 - Projection devices for colour picture display
12.
Aircraft navigation light, combination of an aircraft navigation light and a supplemental exterior aircraft light, and method of operating an exterior aircraft light
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.
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
B60Q 1/00 - Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor
B60Q 1/32 - Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor the devices being primarily intended to indicate the vehicle, or parts thereof, or to give signals, to other traffic for indicating vehicle sides
B60Q 1/46 - Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor the devices being primarily intended to indicate the vehicle, or parts thereof, or to give signals, to other traffic for giving flashing caution signals during drive, other than signalling change of direction, e.g. flashing the headlights
B60Q 1/50 - Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor the devices being primarily intended to indicate the vehicle, or parts thereof, or to give signals, to other traffic for indicating other intentions or conditions, e.g. request for waiting or overtaking
B64D 41/00 - Power installations for auxiliary purposes
13.
Method of emitting an anti-collision light output from an unmanned aerial vehicle, anti-collision light for an unmanned aerial vehicle, and unmanned aerial vehicle comprising the same
A method of emitting an anti-collision light output from an unmanned aerial vehicle includes emitting a plurality of light flashes of different colors within a flash duration interval, with the flash duration interval being at most 0.2 s; wherein the plurality of light flashes within the flash duration interval comprise at least one blue light flash and at least one yellow light flash or wherein the plurality of light flashes within the flash duration interval comprise at least one cyan light flash, at least one magenta light flash, and at least one yellow light flash.
A flight direction indication system for an aerial vehicle having a plurality of rotors includes: for each of the plurality of rotors, at least one rotor blade having a plurality of light sources arranged along a radial extension of the rotor blade; and a control unit, coupled to the plurality of light sources of the rotor blades of the plurality of rotors. The control unit is configured to effect a coordinated control of the plurality of light sources of the rotor blades of the plurality of rotors, with the coordinated control yielding an image or a sequence of images across the plurality of rotors to an observer of the aerial vehicle and to to control the plurality of light sources of the rotor blades of the plurality of rotors on the basis of a momentary flight direction of the aerial vehicle.
A method of indicating a flight direction of an aerial vehicle, having a vehicle body and a plurality of rotors supported by the vehicle body, includes: on the basis of a momentary flight direction of the aerial vehicle, controlling a matrix of light sources, in particular a matrix of LEDs, which are mounted to the vehicle body of the aerial vehicle, to provide an illumination pattern to an observer of the aerial vehicle, with the illumination pattern comprising a flight direction indication, indicative of the momentary flight direction of the aerial vehicle.
A canopy is configured to be mounted to a passenger seat of a passenger transport vehicle, in particular an aircraft. The canopy is foldable between a retracted storage configuration and an extended operational configuration. In the operational configuration, the canopy forms a hood establishing a passenger's personal space below the canopy. The canopy comprises at least one functional device which is configured for modifying a physical characteristics of the personal space. The at least one functional device in particular includes at least one of a lighting device configured for lighting the personal space and a venting device configured for venting the personal space.
An aircraft passenger light includes a reading light unit having a reading light unit and a halo light unit. The reading light unit includes at least one reading light source and is configured for emitting a targeted reading light output. The halo light unit includes at least one halo light source and is configured for emitting a ring shaped halo light output, at least partly surrounding the targeted reading light output.
F21V 7/06 - Optical design with parabolic curvature
F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
F21Y 105/18 - Planar light sources comprising a two-dimensional array of point-like light-generating elements characterised by the overall shape of the two-dimensional array annularPlanar light sources comprising a two-dimensional array of point-like light-generating elements characterised by the overall shape of the two-dimensional array polygonal other than square or rectangular, e.g. for spotlights or for generating an axially symmetrical light beam
An aircraft lighting device includes a circuit board; an LED soldered to the circuit board; an optical element supported by the circuit board and positioned for re-directing at least part of the light emitted by the LED; a magnetic coupling between the circuit board and the optical element; and at least one surface mounted device included in the optical element, such surface mounted device including a pin soldered to the circuit board.
F21V 17/10 - Fastening of component parts of lighting devices, e.g. shades, globes, refractors, reflectors, filters, screens, grids or protective cages characterised by specific fastening means or way of fastening
F21S 41/143 - Light emitting diodes [LED] the main emission direction of the LED being parallel to the optical axis of the illuminating device
An interior aircraft light includes a mounting structure for mounting the interior aircraft light to an aircraft seat; a UV radiation source; and an optical system, configured to direct UV radiation from the UV radiation source towards a floor portion underneath the aircraft seat.
B60Q 3/68 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors characterised by optical aspects using ultraviolet light
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.
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
F21S 4/28 - Lighting devices or systems using a string or strip of light sources with light sources held by or within elongate supports rigid, e.g. LED bars
F21S 10/06 - Lighting devices or systems producing a varying lighting effect flashing, e.g. with rotating reflector or light source
An aircraft beacon light (2) for being mounted to an aircraft fuselage (104) includes: a support structure (4), having a carrier (40), and a stem (42) for supporting the carrier (40) and for spacing the carrier (40) from the aircraft fuselage (104); and a lighting system (6), supported by the support structure (4), the lighting system (6) having a plurality of light sources (60), light optics (62) for re-directing at least a portion of the light emitted by the plurality of light sources (60), and a lens cover (68), with the plurality of light sources (60) and the light optics (62) being arranged between the carrier (40) and the lens cover (68); wherein the aircraft beacon light (2) is configured to emit a red-flashing beacon light output in operation.
A method of operating an aircraft cabin illumination system, having a plurality of light modules with a set spatial distribution across an aircraft cabin, includes receiving an image; mapping the image to the set spatial distribution of the plurality of light modules; generating an illumination command set, including an operating command for each of the plurality of light modules, on the basis of the mapping of the image to the set spatial distribution of the plurality of light modules; and issuing the illumination command set to the plurality of light modules.
B60Q 3/66 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors characterised by optical aspects using light guides for distributing light among several lighting devices
A combined forward navigation and anti-collision light for an aircraft includes a forward navigation light source; a first lens, arranged over the forward navigation light source, with the forward navigation light source and the first lens in operation generating a forward navigation light output; an anti-collision light source; a second lens, arranged over the anti-collision light source, with the anti-collision light source and the second lens in operation generating an anti-collision light output; and a mounting structure, to which the forward navigation light source, the first lens, the anti-collision light source, and the second lens are mounted, wherein the mounting structure provides a common mounting plane, with the forward navigation light source and the anti-collision light source being arranged on the common mounting plane.
A lighting arrangement includes a light source configured for emitting light; a first reflector configured for collimating a first portion of the light emitted by the light source around a main light emission direction (D); and a second reflector arranged opposite to the light source. The second reflector is configured for reflecting a second portion of the light emitted by the light source back towards the light source for being diffusely reflected from the light source.
An aircraft beacon light for an aircraft wing with a foldable wing tip includes a housing, a lens cover, and at least one light source arranged between the housing and the lens cover, wherein the aircraft beacon light is configured to emit flashes of red light in operation, and wherein the housing and the lens cover are shaped to embed the aircraft beacon light into a hinge assembly coupling the foldable wing tip to a main wing portion of the aircraft wing.
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
F21S 43/20 - Signalling devices specially adapted for vehicle exteriors, e.g. brake lamps, direction indicator lights or reversing lights characterised by refractors, transparent cover plates, light guides or filters
Aircraft light for a foldable wing tip of an aircraft, aircraft, and method of operating an aircraft light arranged on a foldable wing tip of an aircraft
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.
An exterior aircraft light for indicating a movement of a foldable wing tip between a folded up position and a laterally extended position includes a light source; and a control unit; wherein the control unit is configured to operate the light source to emit a warning light output in response to a warning light control signal indicative of the movement of the foldable wing tip.
F21V 9/40 - Elements for modifying spectral properties, polarisation or intensity of the light emitted, e.g. filters with provision for controlling spectral properties, e.g. colour, or intensity
An exterior aircraft light includes a housing configured to be mounted to an exterior portion of an aircraft; at least one light source mounted to the housing; a lens cover, cooperating with the housing for forming an inner space of the exterior aircraft light, with light from the at least one light source leaving the exterior aircraft light through the lens cover into an outside environment of the aircraft; and a gasket arranged between the housing and the lens cover, the gasket having at least one flap portion forming at least one check valve for fluid discharge from the inner space of the exterior aircraft light towards the outside environment of the aircraft.
An exterior aircraft light (2, 202, 302) includes a housing (4) configured to be mounted to an exterior portion of an aircraft; at least one light source (6) mounted to the housing (4); a lens cover (10), cooperating with the housing (4) for forming an inner space of the exterior aircraft light, with light from the at least one light source (6) leaving the exterior aircraft light (2, 202, 302) through the lens cover (10) into an outside environment of the aircraft; and a gasket (20) arranged between the housing (4) and the lens cover (10), the gasket (20) having at least one flap portion (22) forming at least one check valve for fluid discharge from the inner space of the exterior aircraft light towards the outside environment of the aircraft.
A cover for an exterior aircraft light includes a lens cover structure, attachable to an exterior aircraft light housing and configured to close the exterior aircraft light housing, wherein the lens cover structure has an inside and an outside and is at least partially made of transparent material; and a wear indicator, attached to the inside of the lens cover structure, the wear indicator having a contrasted pattern visible from the outside of the lens cover structure through the transparent material.
F21S 43/20 - Signalling devices specially adapted for vehicle exteriors, e.g. brake lamps, direction indicator lights or reversing lights characterised by refractors, transparent cover plates, light guides or filters
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
F21V 17/00 - Fastening of component parts of lighting devices, e.g. shades, globes, refractors, reflectors, filters, screens, grids or protective cages
31.
Aircraft beacon light and aircraft comprising an aircraft beacon light
An aircraft beacon light includes a mounting plate having a central portion; a plurality of light sources arranged on the mounting plate around the central portion and facing away from the mounting plate; and a lens structure arranged over the plurality of light sources, wherein the lens structure is configured to reflect a first portion of light emitted by the plurality of light sources laterally outwards via total internal reflection; wherein the aircraft beacon light is configured to emit flashes of red light in operation.
An aircraft light comprises at least one light source; at least one sensor, an operating mode selector, and a transmitter. The sensor is configured for detecting current operational conditions and providing at least one corresponding sensor signal. The operating mode selector configured for determining a suitable light emission of the at least one light source based on the at least one sensor signal. The operating mode selector is further configured for determining the amount of electrical power needed for generating the determined light emission. The transmitter configured for transmitting a power request signal indicating the determined amount of electrical power to a power supply.
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.
An aircraft vertical stabilizer illumination light, the light includes a LED group, having a plurality of LEDs; an optical system, having at least one optical element, the optical system being associated with the LED group for shaping a light output from the light emitted by the LED group; an image generator, arranged within the aircraft vertical stabilizer illumination light for being oriented towards the vertical stabilizer, the image generator being configured to provide image data of the vertical stabilizer; and a controller, coupled to the image generator for receiving the image data; wherein the controller is configured to operate the aircraft vertical stabilizer illumination light in a plurality of operating modes.
An exterior aircraft light includes 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 the housing having a front end region and a rear end region, wherein the housing is configured to be mounted on a tail portion of a fuselage of an aircraft; at least one first light source, arranged in the rear end region of the housing, for providing aircraft rearward signal lighting; and a plurality of second light sources, which are arranged spaced along the length (L) of the housing for a distributed illumination of a stabilizer of the aircraft.
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.
Exterior aircraft light comprising at least one switchable illumination circuits which comprises light sources, a temperature detector, a switch, and a control circuit
An exterior aircraft light comprises at least one switchable illumination circuit. Each of the at least one switchable illumination circuits comprises at least one light source, a temperature detector configured for detecting the temperature of the at least one light source and providing a temperature signal, an electric switch for selectively switching power flow to the at least one light source on and off, and a control circuit which is coupled to the temperature detector and to the electric switch. The control circuit is configured for driving the electric switch based on the temperature signal provided by the temperature detector to repeatedly switch power flow to the at least one light source on and off.
An aircraft beacon light is provided for emitting flashes of red light into an environment around an aircraft. The aircraft beacon light includes a support plate having a central portion; a plurality of LEDs, arranged on the support plate around the central portion and facing away from the support plate; an annular light splitting element, having a proximate side arranged over and facing the plurality of LEDs, wherein the proximate side has reflective portions and transmissive portions; and at least one light conditioning element for redirecting light having passed through the transmissive portions of the proximate side of the annular light splitting element.
B60Q 1/30 - Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor the devices being primarily intended to indicate the vehicle, or parts thereof, or to give signals, to other traffic for indicating rear of vehicle, e.g. by means of reflecting surfaces
An exterior aircraft light unit includes at least two light sources. Each light source is provided with a variable current bypass component. Each variable current bypass component is configured to allow bypassing an adjustable electric current by the respective light source.
H05B 45/14 - Controlling the intensity of the light using electrical feedback from LEDs or from LED modules
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
H02H 3/08 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection responsive to excess current
H05B 45/00 - Circuit arrangements for operating light-emitting diodes [LED]
F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
40.
EXTERIOR AIRCRAFT LIGHT UNIT AND AIRCRAFT COMPRISING THE SAME
An exterior aircraft light unit (2) includes at least two light sources (8). Each light source (8) is provided with a variable current bypass component (12). Each variable current bypass component (12) is configured to allow bypassing an adjustable electric current by the respective light source (8).
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
F21V 25/10 - Safety devices structurally associated with lighting devices coming into action when lighting device is over-loaded, e.g. thermal switch
F21K 9/00 - Light sources using semiconductor devices as light-generating elements, e.g. using light-emitting diodes [LED] or lasers
41.
Aircraft cabin lighting arrangement for illuminating a common space of an aircraft, aircraft comprising the same, and method of operating an aircraft cabin lighting arrangement
An aircraft cabin lighting arrangement for illuminating a common space of an aircraft, includes a light output lens for passing light for illuminating said common space of the aircraft, a plurality of light sources having different light emission spectra, the plurality of light sources being arranged for light emission through the light output lens, and a detector for detecting a person's presence in the common space. The aircraft cabin lighting arrangement has at least a nominal day time mode of operation having a first light output, an intermediate mode of operation having a second light output, and a nominal night time mode of operation, and is configured to switch from the nominal night time mode of operation to the intermediate mode of operation as a response to the detector detecting a person's presence in the common space.
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
B60Q 3/60 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors characterised by optical aspects
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.
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
F21V 5/04 - Refractors for light sources of lens shape
F21V 17/10 - Fastening of component parts of lighting devices, e.g. shades, globes, refractors, reflectors, filters, screens, grids or protective cages characterised by specific fastening means or way of fastening
43.
Drain valve, exterior aircraft light unit and power supply box
A drain valve for draining liquid from an enclosed space comprises a movable plunger, which is movable between a closed position in which the plunger does not allow liquid to flow through the drain valve, and at least one open position, in which the plunger allows liquid to flow through the drain valve; and an elastic element, which is configured to urge the movable plunger into its closed position. The plunger is provided with at least one duct extending through the plunger and allowing fluid to flow through the drain valve when the plunger is positioned in its closed position, wherein said at least one duct is closed by a semi-permeable medium, which is permeable for air and water vapor and impermeable for liquid water.
F16K 1/32 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces Details
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
F21S 45/30 - Ventilation or drainage of lighting devices
F21V 31/03 - Gas-tight or water-tight arrangements with provision for venting
F16K 15/02 - Check valves with guided rigid valve members
F16K 24/00 - Devices, e.g. valves, for venting or aerating enclosures
44.
Combined aircraft wing scan and runway turn-off light unit and aircraft comprising the same
A combined aircraft wing scan and runway turn-off light unit includes a housing for mounting the combined aircraft wing scan and runway turn-off light unit to a side portion of a fuselage of an aircraft; at least one light source; and an optical system for shaping a light emission distribution of the combined aircraft wing scan and runway turn-off light unit; wherein the light emission distribution comprises a first illumination region for illuminating a wing region of the aircraft and a second illumination region for illuminating a lateral forward airfield region.
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
F21S 43/20 - Signalling devices specially adapted for vehicle exteriors, e.g. brake lamps, direction indicator lights or reversing lights characterised by refractors, transparent cover plates, light guides or filters
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.
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.
SS), and a refractive optical element having an inner surface and an outer surface, with at least one of the inner surface and the outer surface being non-spherical, the refractive optical element being arranged over the light source and being attached to the support portion.
F21S 43/20 - Signalling devices specially adapted for vehicle exteriors, e.g. brake lamps, direction indicator lights or reversing lights characterised by refractors, transparent cover plates, light guides or filters
An LED light unit, in particular for a passenger transportation vehicle, such as an aircraft, a road vehicle, a ship or a rail car, has a support portion a light source having at least one LED, the light source being arranged on the support portion, and a refractive optical element having an inner surface and an outer surface the refractive optical element being attached to the support portion and being arranged over the light source. The refractive optical element has a chamfer portion adjacent the support portion, wherein at least one of the inner surface and the outer surface has at least one chamfer surface in the chamfer portion.
F21S 41/14 - Illuminating devices specially adapted for vehicle exteriors, e.g. headlamps characterised by the light source characterised by the type of light source
F21S 41/20 - Illuminating devices specially adapted for vehicle exteriors, e.g. headlamps characterised by refractors, transparent cover plates, light guides or filters
F21S 43/20 - Signalling devices specially adapted for vehicle exteriors, e.g. brake lamps, direction indicator lights or reversing lights characterised by refractors, transparent cover plates, light guides or filters
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
A ground illumination aircraft light unit includes a mounting portion, which is configured for mounting the light unit to an aircraft; a transparent cover, which is mounted to the mounting portion and in combination with the mounting portion defines an interior space of the light unit; and at least one light source, which is arranged within the interior space of the light unit and which is configured for emitting light for illuminating an airfield in the vicinity of the aircraft. The light unit is configured to emit predominantly p-polarized light in a predefined spatial sector; and to emit non-polarized light in an area outside said predefined spatial sector.
F21S 41/135 - Illuminating devices specially adapted for vehicle exteriors, e.g. headlamps characterised by the light source characterised by the type of emitted light polarised
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
F21S 41/147 - Light emitting diodes [LED] the main emission direction of the LED being angled to the optical axis of the illuminating device
F21S 41/20 - Illuminating devices specially adapted for vehicle exteriors, e.g. headlamps characterised by refractors, transparent cover plates, light guides or filters
G02B 27/28 - Optical systems or apparatus not provided for by any of the groups , for polarising
50.
Method of operating an aircraft headlight system, aircraft headlight system, and aircraft comprising the same
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.
H05B 33/08 - Circuit arrangements for operating electroluminescent light sources
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
F21S 41/663 - Illuminating devices specially adapted for vehicle exteriors, e.g. headlamps characterised by a variable light distribution by acting on light sources by switching light sources
F21S 41/19 - Attachment of light sources or lamp holders
F21S 41/153 - Light emitting diodes [LED] arranged in one or more lines arranged in a matrix
F21S 41/145 - Light emitting diodes [LED] the main emission direction of the LED being parallel to the optical axis of the illuminating device the main emission direction of the LED being opposite to the main emission direction of the illuminating device
A lighting system of an aircraft cabin includes a plurality of light units disposed at a plurality of locations within the aircraft cabin, wherein each of the plurality of light units includes at least one infrared light source, with an emission of infrared light across the aircraft cabin resulting from an operation of the at least one infrared light source of the plurality of light units.
B60Q 3/00 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
B60Q 3/46 - Emergency lighting, e.g. for escape routes
B60Q 3/40 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors specially adapted for specific vehicle types
B60Q 3/68 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors characterised by optical aspects using ultraviolet light
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
52.
Exterior aircraft light unit and method of disabling a light output of an exterior aircraft light unit
An exterior aircraft light unit includes a power input coupleable to an aircraft on-board power supply; at least one LED coupled to the power input for receiving power from the aircraft on-board power supply and configured to emit a light output; an optical sensor arranged for sensing an intensity detection portion of the light output and configured to output a detection signal indicative of an intensity level of the light output; an end of life detector, coupled to the optical sensor for receiving the detection signal and configured to determine an end of life condition; and a fuse circuit coupled to the end of life detector; wherein the fuse circuit is configured to irreversibly disable an LED circuit board upon the end of life detector communicating the end of life condition to the fuse circuit.
An exterior aircraft light unit (2) includes a power input (4) coupleable to an aircraft on-board power supply (40); at least one LED (12) coupled to the power input for receiving power from the aircraft on-board power supply and configured to emit a light output; an optical sensor (16) arranged for sensing an intensity detection portion (28) of the light output and configured to output a detection signal indicative of an intensity level of the light output; an end of life detector (30), coupled to the optical sensor for receiving the detection signal and configured to determine an end of life condition; and a fuse circuit (18) coupled to the end of life detector; wherein the at least one LED and the fuse circuit are arranged on an LED circuit board (10) and wherein the fuse circuit is configured to irreversibly disable the LED circuit board upon the end of life detector communicating the end of life condition to the fuse circuit.
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
F21K 9/00 - Light sources using semiconductor devices as light-generating elements, e.g. using light-emitting diodes [LED] or lasers
B64F 5/60 - Testing or inspecting aircraft components or systems
H05B 45/58 - Circuit arrangements for operating light-emitting diodes [LED] responsive to malfunctions or undesirable behaviour of LEDsCircuit arrangements for operating light-emitting diodes [LED] responsive to LED lifeProtective circuits involving end of life detection of LEDs
54.
Exterior aircraft light unit, helicopter, and airplane
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.
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
F21S 43/19 - Attachment of light sources or lamp holders
F21S 43/20 - Signalling devices specially adapted for vehicle exteriors, e.g. brake lamps, direction indicator lights or reversing lights characterised by refractors, transparent cover plates, light guides or filters
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
F21Y 113/10 - Combination of light sources of different colours
An aircraft head light comprises: a plurality of lighting arrangements, each lighting arrangement comprising a light source and a generally parabolic reflector surrounding the respective light source. The plurality of lighting arrangements are arranged in a side-by-side relationship, with the generally parabolic reflectors of adjacent lighting arrangements having respective reflector contact sections. For at least one adjacent pair of the plurality of lighting arrangements, said adjacent pair comprising a first lighting arrangement and a second lighting arrangement the reflector contact section of the generally parabolic reflector of the first lighting arrangement is parabolic and the reflector contact section of the generally parabolic reflector of the second lighting arrangement is non-parabolic.
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
F21V 5/04 - Refractors for light sources of lens shape
F21V 7/06 - Optical design with parabolic curvature
F21V 13/04 - Combinations of only two kinds of elements the elements being reflectors and refractors
F21V 21/005 - Supporting, suspending, or attaching arrangements for lighting devicesHand grips for several lighting devices in an end-to-end arrangement, i.e. light tracks
F21S 41/143 - Light emitting diodes [LED] the main emission direction of the LED being parallel to the optical axis of the illuminating device
F21S 41/255 - Lenses with a front view of circular or truncated circular outline
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.
B60Q 1/14 - Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor the devices being primarily intended to illuminate the way ahead or to illuminate other areas of way or environments the devices being headlights having dimming means
H05B 33/08 - Circuit arrangements for operating electroluminescent light sources
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
B60Q 1/24 - Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor the devices being primarily intended to illuminate the way ahead or to illuminate other areas of way or environments for lighting other areas than only the way ahead
57.
Exterior airplane light unit and method of warning ground personnel
An exterior airplane light unit includes a housing and a lens cover, the housing and the lens cover being shaped to embed the exterior airplane light unit into a side portion of a fuselage of an airplane in front of a wing root section of the airplane, with the lens cover blending into the side portion of the fuselage of the airplane, and at least one light source and at least one optical system, with the at least one light source and the at least one optical system being arranged between the housing and the lens cover and being arranged to direct a warning light output towards an engine of the airplane.
A helicopter anti-bird-collision system including a search light (2) and a control unit (35) which is configured for operating the search light (2) in a flash light mode by switching the search light periodically on and off.
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
B60Q 1/46 - Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor the devices being primarily intended to indicate the vehicle, or parts thereof, or to give signals, to other traffic for giving flashing caution signals during drive, other than signalling change of direction, e.g. flashing the headlights
A01M 29/10 - Scaring or repelling devices, e.g. bird-scaring apparatus using visual means, e.g. scarecrows, moving elements, specific shapes, patterns or the like using light sources, e.g. lasers or flashing lights
B60Q 1/24 - Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor the devices being primarily intended to illuminate the way ahead or to illuminate other areas of way or environments for lighting other areas than only the way ahead
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
A helicopter search light comprises: a lighting arrangement, having at least one light source, the lighting arrangement having an adjustable light output; a light detector, which is configured for detecting light emitted by the at least one light source and 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 which is configured for controlling the adjustable light output of the lighting arrangement of the helicopter search light depending on the detection signal provided by the light detector.
An exterior aircraft light unit (2) includes a lens cover (50) and at least one light source (6, 6′) for emitting light through the lens cover. The lens cover has an aerodynamic front edge (52), separating an impinging air stream during flight, and an aerodynamic front region (54) around the aerodynamic front edge. The light emitted by the at least one light source exits the lens cover only outside the aerodynamic front region.
An exterior aircraft light includes a mounting board, having an upper side, a lower side and a plurality of side faces; at least one LED, arranged on the upper side of the mounting board; and a mounting board enclosure and lens structure, wherein the mounting board enclosure and lens structure comprises a lens arranged over the at least one LED for shaping an output light intensity distribution of the exterior aircraft light and a covering layer arranged on the upper side, the lower side and the plurality of side faces of the mounting board, wherein the mounting board enclosure and lens structure is an integral silicone structure.
F21S 41/37 - Illuminating devices specially adapted for vehicle exteriors, e.g. headlamps characterised by reflectors characterised by their material, surface treatment or coatings
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
F21V 5/04 - Refractors for light sources of lens shape
An exterior aircraft light unit includes a support plate, an LED, mounted to the support plate, a near end of life detector for sensing a light output level of the LED, the near end of life detector being mounted to the support plate, and a transparent optical element for shaping an output light intensity distribution of the exterior aircraft light unit, wherein the transparent optical element jointly encases the LED and the near end of life detector, with light from the LED reaching the near end of life detector through the transparent optical element.
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
F21V 13/04 - Combinations of only two kinds of elements the elements being reflectors and refractors
F21V 17/06 - Fastening of component parts of lighting devices, e.g. shades, globes, refractors, reflectors, filters, screens, grids or protective cages onto or by the lamp holder
H05B 33/08 - Circuit arrangements for operating electroluminescent light sources
F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
An exterior aircraft light unit comprises a housing defining an interior space for accommodating at least one light source; and a hygroscopic material, which is arranged inside the interior space for absorbing water and/or moisture from inside the interior space.
An overhead aircraft passenger service unit, which is configured to be placed above the passenger seats within an aircraft cabin, comprises at least one cavity for housing at least one oxygen mask and at least one removable cover, which at least partially covers an opening of the cavity. The removable cover houses and/or supports at least one functional component.
An overhead aircraft passenger service unit (2), which is configured to be placed above the passenger seats within an aircraft cabin, comprises at least one cavity (9) for housing at least one oxygen mask (16) and at least one removable cover (10), which at least partially covers an opening of the cavity (9). The removable cover (10) houses and/or supports at least one functional component (4, 6, 8, 12, 14).
An exterior aircraft light unit (2) comprises a housing (12) defining an interior space (14) for accommodating at least one light source (4); and a hygroscopic material (24), which is arranged inside the interior space (14) for absorbing water and/or moisture from inside the interior space (14).
A dynamic exterior aircraft light unit, mounted to an aircraft for illuminating an aircraft environment, includes an LED group with a plurality of LEDs, and an optical system with at least one optical element. The optical system being associated with the LED group for shaping an output light intensity distribution from the light emitted by the LED group and the LED group and the optical system are stationary within the dynamic exterior aircraft light unit.
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
F21V 23/04 - Arrangement of electric circuit elements in or on lighting devices the elements being switches
B60Q 1/08 - Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor the devices being primarily intended to illuminate the way ahead or to illuminate other areas of way or environments the devices being headlights adjustable, e.g. remotely-controlled from inside vehicle automatically
F21S 41/143 - Light emitting diodes [LED] the main emission direction of the LED being parallel to the optical axis of the illuminating device
F21S 41/255 - Lenses with a front view of circular or truncated circular outline
F21S 41/663 - Illuminating devices specially adapted for vehicle exteriors, e.g. headlamps characterised by a variable light distribution by acting on light sources by switching light sources
F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
B60Q 1/12 - Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor the devices being primarily intended to illuminate the way ahead or to illuminate other areas of way or environments the devices being headlights adjustable, e.g. remotely-controlled from inside vehicle automatically due to steering position
F21Y 105/10 - Planar light sources comprising a two-dimensional array of point-like light-generating elements
An aircraft LED light unit comprises at least one printed circuit board which comprises at least one metal core layer and at least one dielectric layer, and at least one LED disposed on the printed circuit board and which comprises an anode and a cathode for electrically coupling to a power source. One of the anode and cathode of the at least one LED is connected to an electrical conductor which is disposed on the dielectric layer and is coupled to a first terminal of the power source, wherein the dielectric layer electrically isolates the electrical conductor from the metal core layer, and the other one of the anode and cathode of the at least one LED is connected to the metal core layer of the at least one printed circuit board, wherein the metal core layer is coupled to a second terminal of the power source.
H05K 1/18 - Printed circuits structurally associated with non-printed electric components
F21V 23/04 - Arrangement of electric circuit elements in or on lighting devices the elements being switches
H05K 3/34 - Assembling printed circuits with electric components, e.g. with resistor electrically connecting electric components or wires to printed circuits by soldering
69.
Aircraft interior light unit and method of operating an aircraft interior light unit
An aircraft interior light unit having a light output over an extended light emission area includes a flat light distribution body having a front surface, through which the light output is coupled out, and a back surface, wherein at least one of the front surface and the back surface of the flat light distribution body has a plurality of surface irregularities.
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
G02B 6/00 - Light guidesStructural details of arrangements comprising light guides and other optical elements, e.g. couplings
G09F 9/302 - Indicating arrangements for variable information in which the information is built-up on a support by selection or combination of individual elements in which the desired character or characters are formed by combining individual elements characterised by the form or geometrical disposition of the individual elements
G09F 9/33 - Indicating arrangements for variable information in which the information is built-up on a support by selection or combination of individual elements in which the desired character or characters are formed by combining individual elements being semiconductor devices, e.g. diodes
G09F 13/04 - Signs, boards, or panels, illuminated from behind the insignia
An exterior helicopter light unit (2) with a dynamic output light intensity distribution includes a plurality of LEDs (30), and an optical system (32) for shaping the output light intensity distribution from light emitted by the plurality of LEDs (30), wherein each of the plurality of LEDs (30) contributes to the output light intensity distribution in an LED-specific output direction region, wherein at least a portion of the plurality of LEDs (30) are individually dimmable, with a level of dimming for each of said portion of the plurality of LEDs (30) in operation being set depending on a distance of the exterior helicopter light unit (2) to ground (200) in the respective LED-specific output direction region.
A rotorcraft winch lighting device, which is attachable to a rotorcraft winch, mounted to a rotorcraft such as a helicopter, the rotorcraft winch including a stationary portion and a mobile portion which is movable with respect to the stationary portion, includes: a stationary unit including a stationary coil and a mobile unit. The mobile unit is movable with respect to the stationary unit and includes at least one light source, at least one electrical storage device, and at least one mobile coil, which is electrically connected to the electrical storage device and/or the at least one light source. The stationary coil and the mobile coil are configured for transferring electrical energy from the stationary unit to the mobile unit when the at least one mobile coil is positioned in an energy transfer position in the vicinity of the at least one stationary coil.
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
B64D 1/22 - Taking-up articles from earth's surface
B64F 1/12 - Ground or aircraft-carrier-deck installations for anchoring aircraft
H02J 5/00 - Circuit arrangements for transfer of electric power between ac networks and dc networks
H02J 7/02 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from AC mains by converters
A rotorcraft winch lighting device (15, 16), which is attachable to a rotorcraft winch (2), mounted to a rotorcraft such as a helicopter (44), the rotorcraft winch (2) including a stationary portion (3) and a mobile portion (6, 16, 18) which is movable with respect to the stationary portion (3), includes: a stationary unit (15) including a stationary coil (8) and a mobile unit (16). The mobile unit (16) is movable with respect to the stationary unit (15) and includes at least one light source (26), at least one electrical storage device (40), and at least one mobile coil (38), which is electrically connected to the electrical storage device (40) and/or the at least one light source (26). The stationary coil (8) and the mobile coil (38) are configured for transferring electrical energy from the stationary unit (15) to the mobile unit (16) when the at least one mobile coil (38) is positioned in an energy transfer position in the vicinity of the at least one stationary coil (8).
An aircraft vertical stabilizer illumination light unit, configured for being arranged in a rotatable horizontal stabilizer of an aircraft and for being oriented towards a vertical stabilizer of the aircraft for illuminating the vertical stabilizer, includes an LED group, having a plurality of LEDs, and an optical system, having at least one optical element, the optical system being associated with the LED group for shaping an output light intensity distribution from the light emitted by the LED group.
An aircraft vertical stabilizer illumination light unit (2), configured for being arranged in a rotatable horizontal stabilizer (102) of an aircraft (100) and for being oriented towards a vertical stabilizer (104) of the aircraft (100) for illuminating the vertical stabilizer (104). The illumination light unit is configured to be operated in a plurality of operating modes, with a respective subset of a plurality of LEDs being switched on in each of the plurality of operating modes and with a different output light in- tensity distribution (120, 130, 140) being emitted by the aircraft vertical stabilizer illumination light unit (2) in each of the plurality of operating modes, with a selec- tion of the operating mode being carried out in response to a rotation angle of the rotatable horizontal stabilizer (102).
An aircraft landing light unit includes a plurality of LEDs, an optical system associated with the plurality of LEDs for shaping a light output of the aircraft landing light unit for illuminating an aircraft environment, a control unit for controlling the plurality of LEDs, and a photo detector arranged for detecting light, emitted by the plurality of LEDs, output via the optical system and reflected by atmospheric haze, such as clouds, fog, rain and snow, wherein the control unit is coupled to the photo detector and is configured to control the plurality of LEDs on the basis of the light detected by the photo detector, thereby adjusting the light output of the aircraft landing light unit to the atmospheric haze.
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
H05B 33/08 - Circuit arrangements for operating electroluminescent light sources
B60Q 1/14 - Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor the devices being primarily intended to illuminate the way ahead or to illuminate other areas of way or environments the devices being headlights having dimming means
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
F21V 5/04 - Refractors for light sources of lens shape
A dynamic exterior aircraft light unit includes a plurality of LEDs, with at least two subsets of the plurality of LEDs being separately, an optical system for transforming light output from the plurality of LEDs into at least two light emission distributions, a control unit for controlling the plurality of LEDs, and a photo detector arranged to detect light, emitted by the dynamic exterior aircraft light unit as part of the at least two light emission distributions and reflected by the aircraft environment, and configured to output a light detection signal.
An exterior aircraft lighting device comprises: at least one light source; an optical element having a light entry side facing the at least one light source and a light exit side and being configured for modifying light emitted by the at least one light source; at least one photo detector, which is configured and arranged for detecting a portion of the light emitted by the at least one light source, which is reflected by the light entry side of the at least one optical element, the photo detector providing a detection value, representing the amount of detected light; and a control and evaluation unit which is configured for evaluating the state of wear of the at least one light source based on the detection value provided by the at least one photo detector.
An erosion detector for an exterior aircraft lighting device is configured for detecting the state of erosion of an at least partially transparent cover of an exterior aircraft lighting device and includes: at least one light source, which is configured for radiating light onto the at least partially transparent cover; at least one light detection element, which is configured for detecting light reflected by the at least partially transparent cover and for providing a corresponding detection signal; and an evaluation unit, which is configured for evaluating the detection signal for determining the state of erosion of the at least partially transparent cover.
An interior aircraft LED light unit includes at least one printed circuit board, on which a plurality of LEDs are connected to a power source, each one of the plurality of LEDs having a predetermined distance to the power source, and each one of the plurality of LEDs being associated with a respective thermal transfer member having a predetermined size, for transferring heat away from the respective LED, wherein, for at least some of the plurality of LEDs the predetermined size of the respective thermal transfer member varies with the predetermined distance of the LED to the power source.
F21V 29/00 - Protecting lighting devices from thermal damageCooling or heating arrangements specially adapted for lighting devices or systems
F21V 29/10 - Arrangement of heat-generating components to reduce thermal damage, e.g. by distancing heat-generating components from other components to be protected
An exterior aircraft navigation light for an aircraft having a nominal forward flight direction and being able to fly into the nominal forward flight direction as well as into a plurality of further flight directions, such as sideways or backwards, has at least one light emission unit and control circuitry coupled to the at least one light emission unit, wherein the exterior aircraft navigation light is configured such that each of the at least one light emission unit has a unit-specific light emission direction that has a predefined horizontal angle with respect to the nominal forward flight direction, and wherein each of the at least one light emission unit includes a multi-color light source configured to emit red light, white light and green light, and an optical system for conditioning the red light, the white light and the green light emitted by the multi-color light source.
An at least partially transparent exterior aircraft light cover includes at least one protrusion provided at a lateral end of the exterior aircraft light cover, wherein the at least one protrusion is configured to be introduced into a corresponding reception provided at an exterior aircraft light casing and wherein the protrusion is formed for allowing the cover to pivot, with the protrusion providing a fulcrum, when the protrusion is introduced into the reception. The at least partially transparent exterior aircraft light cover further includes at least one fixing device, which is provided in a pivotable portion of the cover and which is configured for removably fixing said pivotable portion to the casing for preventing a pivoting motion thereof.
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
F21V 5/04 - Refractors for light sources of lens shape
F21V 17/10 - Fastening of component parts of lighting devices, e.g. shades, globes, refractors, reflectors, filters, screens, grids or protective cages characterised by specific fastening means or way of fastening
F21V 31/00 - Gas-tight or water-tight arrangements
82.
Layer material for arranging on a rotor blade tip of a helicopter, helicopter light system, and helicopter comprising the same
In an embodiment, a layer material configured to be arranged on a rotor blade tip of a helicopter comprises at least one light emitting or reflecting section that emits or reflects light after being exposed to a remote light source. The light source can be arranged on the body of the helicopter.
An exterior aircraft light includes a base plate and a plurality of lighting units arranged on the base plate, wherein each of the plurality of lighting units includes an elongated LED light source for emitting light, the elongated LED light source having a light emitting surface with a longitudinal extension and a transverse extension, with the longitudinal extension being greater than the transverse extension and with a projection of the longitudinal extension onto the base plate defining an orientation direction of the elongated LED light source, and a collimating optical system for collimating the light emitted by the elongated LED light source towards a main output direction, wherein the plurality of lighting units has at least a first lighting unit and a second lighting unit.
A light unit with an extended light emission surface includes a light source, and a flat light distribution body having a first principal surface and a second principal surface disposed on opposite sides of the flat light distribution body, wherein the light source is positioned outside of the flat light distribution body, with light emitted by the light source being coupled into the flat light distribution body and being propagated within the flat light distribution body via total internal reflection at the first and second principal surfaces.
A helicopter search light includes at least one first light source, with the at least one first light source in operation providing a spot light functionality of the helicopter search light, at least one second light source, with the at least one second light source in operation providing a flood light functionality of the helicopter search light, and a switching circuit having a first switching state, with only the at least one first light source being switched on and the helicopter search light providing a pure spot light functionality in the first switching state, and a second switching state, with only the at least one second light source being switched on and the helicopter search light providing a pure flood light functionality in the second switching state.
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
B60Q 1/24 - Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor the devices being primarily intended to illuminate the way ahead or to illuminate other areas of way or environments for lighting other areas than only the way ahead
F21S 8/00 - Lighting devices intended for fixed installation
86.
Interior aircraft light unit and method of producing an interior aircraft light unit
An interior aircraft light unit includes at least one light source, in operation emitting light with a source side light intensity distribution, the source side light intensity distribution having a first intensity region and a second intensity region, with the first intensity region having a higher light intensity than the second intensity region, and a semi-transparent layer, disposed between the at least one light source and an outside of the interior aircraft light unit, for transforming the source side light intensity distribution into an adjusted light intensity distribution, wherein the semi-transparent layer has a transparency distribution having a lower degree of transparency in the first intensity region than in the second intensity region, such that the adjusted light intensity distribution is closer to an even light intensity distribution than the source side light intensity distribution.
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
G08B 7/06 - Signalling systems according to more than one of groups Personal calling systems according to more than one of groups using electric transmission
G09F 13/04 - Signs, boards, or panels, illuminated from behind the insignia
G09F 13/10 - Signs, boards, or panels, illuminated from behind the insignia using both translucent and non-translucent layers using transparencies
G09F 21/06 - Mobile visual advertising by aeroplanes, airships, balloons, or kites
F21S 43/00 - Signalling devices specially adapted for vehicle exteriors, e.g. brake lamps, direction indicator lights or reversing lights
A ground illumination aircraft light unit has an operating light emission distribution for illuminating a ground area below an aircraft, wherein the ground illumination aircraft light unit is configured to be mounted to an underside of an aircraft fuselage, and wherein the operating light emission distribution includes a straight downward emission direction normal to the ground area and covers a solid angle of illumination around the straight downward emission direction, wherein the solid angle of illumination is at least 1.3 π sr.
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.
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
F21W 111/06 - Use or application of lighting devices or systems for signalling, marking or indicating, not provided for in groups for aircraft runways or the like
An exterior aircraft light unit includes a mounting structure, an LED arranged on the mounting structure, and an optical system, arranged on the mounting structure for creating an output light emission distribution of the exterior aircraft light unit. The optical system has, in a first cross-sectional plane extending through the LED, a first concave reflector and a second concave reflector, each of the first and second concave reflectors having a proximate end positioned adjacent to the mounting structure and a distal end positioned removed from the mounting structure, with the first and second concave reflectors being arranged on opposite sides of the LED in the first cross-sectional plane, and a refractive optical element arranged between the first and second concave reflectors in the first cross-sectional plane. The distal ends of both the first and second concave reflectors that curve towards each other and have back-tapered shapes.
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
F21V 7/08 - Optical design with elliptical curvature
F21V 13/04 - Combinations of only two kinds of elements the elements being reflectors and refractors
B64D 7/02 - Arrangement of military equipment, e.g. armaments, armament accessories or military shielding, in aircraftAdaptations of armament mountings for aircraft the armaments being firearms
An exterior aircraft light unit includes a mounting structure, a plurality of first light sources arranged on the mounting structure, and a lens cover arranged over the plurality of first light sources, the lens cover having a convex shape at least in a first cross-sectional plane, wherein the plurality of first light sources are arranged in a curved pattern, with the curved pattern having the same direction of curvature as the convex shape of the lens cover in the first cross-sectional plane.
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.
A self-checking emergency light unit includes a power input terminal coupleable to an external power supply for receiving power therefrom, an illumination circuit coupled to the power input terminal, a discharge circuit coupled to the emergency power source, and an operational check module coupled to the emergency power source.
B60L 1/00 - Supplying electric power to auxiliary equipment of electrically-propelled vehicles
B60Q 3/02 - Arrangement of lighting devices for vehicle interior, the mounting or supporting thereof or circuits therefor for lighting passenger or driving compartment
G08B 29/12 - Checking intermittently signalling or alarm systems
H02J 9/00 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
A combined anti-collision and navigation light unit for an aircraft includes a light source, having at least one LED and having a source-side light intensity distribution, and a lens cover with a shape that is configured to transform the source-side light intensity distribution into an output light intensity distribution of the combined anti-collision and navigation light unit.
A status indicating light unit includes a power input terminal, an illumination circuit, comprising at least one LED, a continuous connection circuit, coupled to the illumination circuit and configured to effect a continuous power transfer from a power input terminal to the illumination circuit, a pulsed power reception circuit, coupled to the illumination circuit and configured to draw power from the power input terminal in a pulsed manner and to continuously emit power to the illumination circuit, and a mode selection switch adapted to couple the continuous connection circuit to the power input terminal in a continuous power draw mode, resulting in a continuous power draw pattern of the status indicating light unit, and adapted to couple the pulsed power reception circuit to the power input terminal in a pulsed power draw mode.
An exterior light unit, has an LED in operation emitting light; a reflector, which reflects a first portion of the light emitted by the LED; a first lens, through which the first portion of the light is refracted after being reflected by the reflector; and a second lens, which is an aspherical collimating lens and which is arranged in such a way with respect to the LED that a second portion of the light emitted by the LED has an unobstructed path to the second lens and is collimated by the second lens in a main light output plane. The second portion of the light, when on its way from the LED to the second lens, crosses way with the first portion of the light, when on its way from the reflector to the first lens.
A lighting structure for an exterior vehicle light unit has a light source with a principal light emission direction, at least one LED, a substantially parabolic reflector arranged to reflect light output from the light source in a first output region and to collimate the same in a primary light output direction. The light source is arranged in such a way with respect to the substantially parabolic reflector and the aspherical collimating lens that the principal light emission direction is inclined at an acute angle with respect to the primary light output direction.
An aircraft light comprises a housing, at least one light source to be cooled, the at least one light source being arranged in the housing, a heat sink element thermally coupled to the at least one light source and defining a cooling surface exposable to a cooling airstream for the cooling airstream to flow along the cooling surface in a flow direction. The cooling surface extends between upstream and downstream end portions spaced apart in the flow direction and means for generating a pressure difference between the upstream and downstream end portions of the cooling surface. Due to the pressure difference, a cooling airstream flowing along the cooling surface is created.
F21V 1/20 - Covers for framesFrameless shades characterised by the material the material being glass
F21V 21/00 - Supporting, suspending, or attaching arrangements for lighting devicesHand grips
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
B62D 47/02 - Motor vehicles or trailers predominantly for carrying passengers for large numbers of passengers, e.g. omnibus
F21V 29/02 - Cooling by forcing air over or around the light source (cooling arrangements structurally associated with electric lamps H01J 61/52, H01K 1/58)
F21V 29/60 - Cooling arrangements characterised by the use of a forced flow of gas, e.g. air
F21V 29/71 - Cooling arrangements characterised by passive heat-dissipating elements, e.g. heat-sinks using a combination of separate elements interconnected by heat-conducting means, e.g. with heat pipes or thermally conductive bars between separate heat-sink elements
An aircraft light unit (2), has a support portion (4), a light source having at least one LED (6), the light source being arranged on the support portion (4) and in operation emitting light with a source-side light intensity distribution, and an optical element (8) for transforming the source-side light intensity distribution into an output light intensity distribution. The optical element (8) has at least two transformation segments (10, 20, 30), covering different angular ranges of the source-side light intensity distribution in a first cross-sectional plane. The at least two transformation segments (10, 20, 30) include a first transformation segment (10), with the light from the light source experiencing total internal reflection within the optical element (8) in the first transformation segment (10) and being bundled in a peak region of the output light intensity distribution, and at least one further transformation segment (20, 30), with the light from the light source experiencing refraction only in the at least one further transformation segment (20, 30).
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided forHandling, transporting, testing or inspecting aircraft components, not otherwise provided for
F21V 5/04 - Refractors for light sources of lens shape
G02B 27/09 - Beam shaping, e.g. changing the cross-sectioned area, not otherwise provided for
An autonomous emergency light unit for an aircraft has a power input for receiving power from an external power supply, a rechargeable power source, at least one LED for illuminating the emergency light unit, and a light unit control logic configured to operate the emergency light unit in a plurality of operating states as a response to external control information received and processed by the light unit control logic. The plurality of operating states includes a discharge and illumination state, with the rechargeable power source being discharged over the at least one LED in the discharge and illumination state. The light unit control logic is configured to operate the emergency light unit in the discharge and illumination state as a response to no power being provided at the power input.
H05B 37/00 - Circuit arrangements for electric light sources in general
H05B 33/08 - Circuit arrangements for operating electroluminescent light sources
B60Q 3/02 - Arrangement of lighting devices for vehicle interior, the mounting or supporting thereof or circuits therefor for lighting passenger or driving compartment
B64D 25/00 - Emergency apparatus or devices, not otherwise provided for
F21S 9/02 - Lighting devices with a built-in power supplySystems employing lighting devices with a built-in power supply the power supply being a battery or accumulator
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
H02J 9/02 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which an auxiliary distribution system and its associated lamps are brought into service
F21V 23/04 - Arrangement of electric circuit elements in or on lighting devices the elements being switches
G08B 7/06 - Signalling systems according to more than one of groups Personal calling systems according to more than one of groups using electric transmission
100.
Emergency lighting system for an aircraft and aircraft comprising such emergency lighting system
An emergency lighting system for an aircraft includes an emergency light control unit, having an external power input and at least one external control input for receiving external control commands from at least one of a cockpit crew, a cabin crew, a board computer and an autopilot, and a plurality of autonomous emergency light units, each of the plurality of autonomous emergency light units comprising at least one LED and a rechargeable capacitor. The emergency light control unit is configured to process the external control commands and to communicate emergency light control commands to the plurality of autonomous emergency light units as a response to the external control commands.
H05B 33/08 - Circuit arrangements for operating electroluminescent light sources
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
B60Q 3/02 - Arrangement of lighting devices for vehicle interior, the mounting or supporting thereof or circuits therefor for lighting passenger or driving compartment
H02J 9/06 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over
patents
