An exterior aircraft light comprises: a base structure; at least one light source for emitting light providing a preliminary light output, wherein the at least one light source is arranged on the base structure; and a shutter arrangement for forming a light output of the exterior aircraft light by partially blocking the preliminary light output. The shutter arrangement is coupled to the base structure via a pivoting mechanism. When arranged in different pivoting positions, the shutter arrangement blocks different portions of the preliminary light output.
F21S 41/686 - Blades, i.e. screens moving in a vertical plane
F21S 41/43 - Illuminating devices specially adapted for vehicle exteriors, e.g. headlamps characterised by screens, non-reflecting members, light-shielding members or fixed shades characterised by the shape thereof
2.
AIRCRAFT NAVIGATION LIGHT AND AIRCRAFT COMPRISING THE SAME
An aircraft navigation light comprises a support portion, a light source comprising at least one green LED, the light source being arranged on the support portion, an optical element arranged over the light source for shaping an aircraft navigation light output, and a red light filter. A method of producing an aircraft navigation light comprises the steps of providing a support portion, providing a light source comprising at least one green LED, arranging the light source on the support portion, molding an optical element over the light source, and molding a red light filter over the optical element.
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
F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
An aircraft headlight comprises a housing; a retractable light emission unit, wherein the retractable light emission unit is movable with respect to the housing between a stowed position and an operating position; and an electric motor. The electric motor comprises a casing, which is stationary with respect to the housing; a rotor, which is rotatable with respect to the casing and which is mechanically coupled to the retractable light emission unit for moving the retractable light emission unit between the stowed position and the operating position by rotating the rotor; at least one stationary magnet, which is attached to the casing; and at least one moving permanent magnet, which is attached to the rotor such that, in at least one rotational position of the rotor, the at least one moving permanent magnet is located vis-à-vis the at least one stationary magnet.
An optics support system for an aircraft light comprises: a multi-layer support board, having a main plane of extension; an LED arranged on the multi-layer support board; a first set of leg stands, positioned around the LED, wherein the first set of leg stands provides first abutment surfaces for arranging an optical element, having a corresponding set of legs, over the LED in a first orientation; and a second set of leg stands, positioned around the LED. The second set of leg stands provides second abutment surfaces for arranging the optical element over the LED in a second orientation; and the first abutment surfaces and the second abutment surfaces are at different heights in a z-dimension of the multi-layer support board, orthogonal to the main plane of extension.
F21V 17/02 - Fastening of component parts of lighting devices, e.g. shades, globes, refractors, reflectors, filters, screens, grids or protective cages with provision for adjustment
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
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
INTERIOR AIRCRAFT LIGHTING ASSEMBLY, AIRCRAFT PASSENGER SERVICE UNIT WITH AN INTERIOR AIRCRAFT LIGHTING ASSEMBLY, AND METHOD OF OPERATING AN INTERIOR AIRCRAFT LIGHTING ASSEMBLY
An interior aircraft lighting assembly comprises: at least one infrared lighting device for emitting infrared light; at least one further lighting device for emitting visible light; a lighting assembly controller for controlling an operation of the at least one infrared lighting device and of the at least one further lighting device; a supplementary infrared lighting device controller; and a power supply network, which is configured for supplying electric power from the lighting assembly controller to the at least one further lighting device. The supplementary infrared lighting device controller is tapped into the power supply network. The lighting assembly controller is configured to provide an electric trigger pulse on the power supply network for activating the at least one infrared lighting device.
An aircraft light comprises a light source support board, having a light source side and a back side; and a light source, arranged on the light source side of the light source support board; wherein the light source support board comprises a first metallic layer, the first metallic layer forming conductive traces on the light source side of the light source support board; an isolating layer; a second metallic layer, wherein the isolating layer is arranged between the first metallic layer and the second metallic layer and isolates the second metallic layer from the first metallic layer; and a support board core layer. A cavity is provided in the support board core layer.
An aircraft light includes a light source support board; at least one light source, arranged on a light source side of the light source support board, the at least one light source being arranged to provide an aircraft light output of the aircraft light; a light transmission opening through the light source sup-port board, the light transmission opening extending between the light source side of the light source support board and a back side of the light source support board; an electronics accommodation space on the back side of the light source support board; a first auxiliary support board, arranged in the electronics accommodation space; a second auxiliary support board, arranged in the electronics accommodation space; and an opto-electronic component, arranged on the second auxiliary support board and oriented towards the light transmission opening.
An elongated aircraft cabin light for illuminating a passenger cabin of an aircraft from a ceiling of the passenger cabin comprises: a row arrangement of a plurality of light modules, extending along a longitudinal direction (L) of the elongated aircraft cabin light. Each of the plurality of light modules comprises at least one light source. The plurality of light modules include a plurality of intermediate light modules and, on at least one end of the row arrangement, an end light module. Each of the plurality of intermediate light modules is configured for emitting a downward light output and at least one lateral light output towards at least one lateral side.
B60Q 3/62 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors characterised by optical aspects using light guides
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
9.
AIRCRAFT LIGHT, AIRCRAFT COMPRISING AN AIRCRAFT LIGHT, METHOD OF ASSEMBLING AN AIRCRAFT LIGHT, AND METHOD OF MANUFACTURING A SENSOR CAP FOR AN AIRCRAFT LIGHT
An aircraft light comprises: at least one light source for providing an aircraft light output; a light sensor for detecting a performance level of the aircraft light output; and a sensor cap, arranged over the light sensor and defining a cavity for accommodating the light sensor. The sensor cap has a layered structure comprising: a cap-shaped support layer; a first coating layer, wherein the first coating layer is made of a first metal and is arranged on an inner side of the cap-shaped support layer; and a second coating layer. The second coating layer is made of a second metal and is arranged on the first coating layer.
An aircraft overhead passenger service unit, which is configured to be mounted in a passenger cabin of an aircraft above a passenger seating space, comprises a visual sign structure extending downward from the aircraft overhead passenger service unit. The visual sign structure comprises a signal light and a wall illumination light. The signal light is arranged on a first side of the visual sign structure facing rearward. The signal light comprises at least one first switchable light source. The wall illumination light is arranged on a second side of the visual sign structure facing forward. The wall illumination light comprises at least one second switchable light source and a light directing element. The at least one second switchable light source and the light directing element are arranged to provide a wall illumination light output towards a lateral side of the aircraft overhead passenger service unit.
An aircraft light comprises: a support element, supporting at least one light source; an injection molded optical element, made of light transmissive silicone rubber; and a layer of light transmissive silicone rubber arranged between at least a portion of the injection molded optical element and at least a portion of the support element. The layer of light transmissive silicone rubber provides adhesion between the injection molded optical element and the support element.
An exterior aircraft light comprises a housing defining an interior space; a light output generation unit comprising at least one light source; power supply electronics, coupled to the light output generation unit for driving a light output of the exterior aircraft light and a draining device for draining the interior space. At least one of the light output generation unit and the power supply electronics is arranged within the interior space. The draining device comprises a first drainage tube for receiving fluid, a second drainage tube for receiving fluid; and a fluid discharge port for discharging fluid out of the housing. Each of the first and second drainage tubes comprises a valve mechanism for selectively sealing and opening the respective drainage tube with respect to the interior space.
An exterior aircraft light comprises a housing defining an interior space; a light output generation unit comprising at least one light source; power supply electronics, coupled to the light output generation unit for driving a light out-put of the exterior aircraft light; and a draining device for draining the interior space. The draining device comprises a first drainage tube for receiving fluid, which is to be drained from the interior space; a second drain-age tube for receiving fluid, which is to be drained from the interior space; and a fluid discharge port for discharging fluid out of the housing, wherein the fluid discharge port is in fluid communication with the first drainage tube and with the second drainage tube. Each of the first drainage tube and the second drainage tube comprises a valve mechanism for selectively sealing and opening the respective drainage tube with respect to the interior space.
F21V 31/03 - Gas-tight or water-tight arrangements with provision for venting
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
F21V 15/01 - Housings, e.g. material or assembling of housing parts
F21V 23/02 - Arrangement of electric circuit elements in or on lighting devices the elements being transformers or impedances
14.
Interior aircraft lighting assembly, aircraft passenger service unit with an interior aircraft lighting assembly, and method of operating an interior aircraft lighting assembly
An interior aircraft lighting assembly comprises: at least one infrared lighting device for emitting infrared light; at least one further lighting device for emitting visible light; a lighting assembly controller for controlling an operation of the at least one infrared lighting device and of the at least one further lighting device; a supplementary infrared lighting device controller; and a power supply network, which is configured for supplying electric power from the lighting assembly controller to the at least one further lighting device. The supplementary infrared lighting device controller is tapped into the power supply network. The lighting assembly controller is configured to provide an electric trigger pulse on the power supply network for activating the at least one infrared lighting device.
An aircraft light comprises at least one light source and a local electric power supply for supplying electric power to the at least one light source. The local electric power supply comprises a power supply housing, which is produced by additive manufacturing and comprises a compartment accommodating power supply electronics and at least one hollow cavity, which is delimited from the compartment. The compartment is filled with a potting material. The aircraft light further comprises a plurality of electric connections extending from the power supply electronics through the potting material to the at least one light source for supplying electric power to the at least one light source, thus enabling an aircraft light output of the aircraft light.
An aircraft beacon light includes: a plurality of first LEDs, wherein the plurality of first LEDs emit aviation red light in accordance with Federal Aviation Regulations section 25.1397 at an operating temperature of 25° C.; and a plurality of second LEDs, wherein the plurality of second LEDs are phosphor-converted LEDs of red or reddish orange color; wherein the aircraft beacon light is configured to jointly flash the plurality of first LEDs and the plurality of second LEDs for emitting a red beacon light output.
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
H01L 25/075 - Assemblies consisting of a plurality of individual semiconductor or other solid-state devices all the devices being of a type provided for in a single subclass of subclasses , , , , or , e.g. assemblies of rectifier diodes the devices not having separate containers the devices being of a type provided for in group
H01L 33/30 - Materials of the light emitting region containing only elements of group III and group V of the periodic system
17.
Aircraft light, aircraft comprising an aircraft light, and method of manufacturing an aircraft light
An aircraft light providing a white light output has a light source that comprises a light emitting semiconductor for emitting light having an initial light spectrum; a first light converting material, arranged over the light emitting semiconductor; and a light transmissive layer, covering the first light converting material. A first portion of the light, which is emitted by the light emitting semiconductor, is shifted towards longer wavelengths by the first light converting material. The aircraft light further comprises a second light converting material, which is arranged over the light transmissive layer of the light source and a lens element, which is arranged over the second light converting material, with light exiting the lens element forming at least a portion of the white light output of the aircraft light.
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
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
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
18.
Aircraft headlight, aircraft comprising an aircraft headlight and method of manufacturing an aircraft headlight
An aircraft headlight comprises at least one light source and an integrated, single-piece optical structure. The integrated, single-piece optical structure includes a light transmissive protective cover portion, forming an outer light emission surface of the aircraft headlight, and at least one reflector portion, arranged for directing light that is emitted by the at least one light source through the light transmissive protective cover portion.
F21S 41/43 - Illuminating devices specially adapted for vehicle exteriors, e.g. headlamps characterised by screens, non-reflecting members, light-shielding members or fixed shades characterised by the shape thereof
F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
19.
Multi mode aircraft beacon light and aircraft comprising a multi mode aircraft beacon light
A multi mode aircraft beacon light comprises a mounting portion for mounting the multi mode aircraft beacon light to an aircraft fuselage; at least one visible light source for emitting a visible beacon light output; a plurality of infra-red light sources for emitting an infrared beacon light output; an orientation sensor; and a controller, coupled to the orientation sensor for receiving an orientation sensor signal from the orientation sensor. The controller is configured to determine a mounting orientation of the multi mode aircraft beacon light from the orientation sensor signal, wherein the mounting orientation is indicative of whether the multi mode aircraft beacon light has an upper fuselage mounting position or a lower fuselage mounting position; and to selectively operate the plurality of infrared light sources, depending on the mounting orientation of the multi mode aircraft beacon light.
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
F21S 43/10 - Signalling devices specially adapted for vehicle exteriors, e.g. brake lamps, direction indicator lights or reversing lights characterised by the light source
F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
Exterior aircraft light with cover erosion monitoring, aircraft comprising such exterior aircraft light, and method of monitoring erosion of a light transmissive cover
An exterior aircraft light with cover erosion monitoring, the exterior aircraft light comprises: a support; at least one light source, arranged on the support; a light transmissive cover, arranged over the at least one light source, the light transmissive cover having a forward facing portion and a rear-ward facing portion; a first light sensor, arranged to receive light emitted by the at least one light source and reflected towards the first light sensor by the forward facing portion of the light transmissive cover; and a second light sensor, arranged to receive light emitted by the at least one light source and reflected towards the second light sensor by the rearward facing portion of the light transmissive cover.
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
F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
Exterior aircraft light, comprising a light source having a first electrode and a second electrode and a light source support for supporting the light source, wherein the light source support comprises conductive traces for supplying electric energy to the light source; and wherein the light source support comprises a first group of electric contact areas, which are spaced from each other and which are electrically connected with each other, and a second group of electric contact areas, which are spaced from each other and which are electrically connected with each other. The first group of electric contact areas and the second group of electric contact areas form an extended electric contact structure that allows for the light source to be positioned on the light source support in a plurality of different positions.
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
F21S 41/19 - Attachment of light sources or lamp holders
H05K 1/11 - Printed elements for providing electric connections to or between printed circuits
22.
LIGHT MODULE FOR AN ELONGATED INTERIOR AIRCRAFT LIGHT, ELONGATED INTERIOR AIRCRAFT LIGHT, AIRCRAFT, AND METHOD OF INSTALLING AN ELONGATED INTERIOR AIRCRAFT LIGHT IN AN AIRCRAFT
A light module for an elongated interior aircraft light includes: a plurality of light sources, forming an array of light sources that extends between a first lateral end portion of the light module and a second lateral end portion of the light module; and an elongated light transmissive cover that is arranged over the array of light sources, wherein the elongated light transmissive cover allows a forward light output portion, emitted by the plurality of light sources towards the elongated light transmissive cover, to pass through; wherein, at at least one of the first lateral end portion and the second lateral end portion, a light output boosting lateral end cap is provided, wherein the light output boosting lateral end cap is shaped to mesh with a neighboring lateral end cap of a neighboring light module.
B60Q 3/64 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors characterised by optical aspects using light guides for a single lighting device
B60Q 3/74 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors characterised by the purpose for overall compartment lightingArrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors characterised by the purpose for overall compartment lighting in combination with specific lighting, e.g. room lamps with reading lamps
ELECTRIC AIRCRAFT EMERGENCY POWER SUPPLY MODULE, AIRCRAFT EMERGENCY LIGHTING MODULE, AND METHOD OF CHARGING A POWER CELL OF AN ELECTRIC AIRCRAFT EMERGENCY POWER SUPPLY MODULE
An electric aircraft emergency power supply module, which is connectable to an electric charger, comprises: at least one electric power cell for storing and supplying electric energy; at least one voltage sensor for measuring the electric voltage (U) of the at least one electric power cell; and a controller for controlling a charging of the at least one electric power cell. Controlling the charging of the at least one electric power cell includes receiving a voltage indication signal (U(t)), indicative of the electric voltage (U) of the at least one electric power cell over time (t), from the at least one voltage sensor; determining the second derivative (U″(t)) of the voltage indication signal (U(t)) with respect to time (t); and on the basis of a positive-to-negative zero crossing of the second derivative (U″(t)) of the voltage indication signal (U(t)), simulating the behavior of a temperature sensitive element.
H02J 9/04 - 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
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
24.
Exterior aircraft light with integrated light output monitoring, aircraft comprising such exterior aircraft light, and method for monitoring a light output of an exterior aircraft light
An exterior aircraft light with integrated light output monitoring includes a light source support, at least one light source, arranged on an outward facing side of the light source support, an aperture in the light source support, a light collection surface, arranged to direct an output monitoring light portion of the light, emitted by the at least one light source, through the aperture in a predefined angular range with respect to the light source support. The light also includes a light detector, arranged on a back side of the light source support, and a total internal reflection optical element, arranged to direct the output monitoring light portion, having travelled through the aperture in the predefined angular range with respect to the light source support, to the light detector via total internal reflection.
An aircraft reading light with a color-tunable reading light output includes: a white light source for emitting white light; a colored light source for emitting colored light; and an optical element, which is arranged for directing colored light that is emitted by the colored light source onto the white light source for being diffusely reflected at the white light source. The colored light source is controllable independently from the white light source.
An aircraft beacon light includes a plurality of primary light sources for emitting light into at least two spatial sectors, wherein the at least two spatial sectors include a forward sector and at least one of an aft sector, a starboard lateral sector, and a portside lateral sector; and a light transmissive cover, which covers the plurality of primary light sources. The plurality of primary light sources are arranged and configured for providing an FAR-compliant aircraft beacon light output of the aircraft beacon light, in case of the light transmissive cover being in a non-eroded state. The aircraft beacon light also includes at least one booster light source for selectively emitting a booster light output into the forward sector. The at least one booster light source is controllable independently of the plurality of primary light sources.
Exterior aircraft light, aircraft comprising an exterior aircraft light, and method for providing an extent of erosion of an exterior surface of a light transmissive cover of an exterior aircraft light
An exterior aircraft light includes a support and a light transmissive cover having a light transmissive body with an interior surface and an exterior surface. The light includes at least one light source arranged between the support and the light transmissive cover; and a first light detector. The light transmissive cover has a first light guide path within the light transmissive body from a first light entry region to a first light exit region, wherein the first light detector is arranged to receive light that travels along the first light guide path and that exits the light transmissive cover at the first light exit region. The first light detector is configured to provide sensor measurements corresponding to the amount of light incident on the first light detector.
A protective cover for a fuselage-mounted exterior aircraft light includes a fuselage-facing mounting side for mounting the protective cover to an exterior aircraft light housing or to an exterior skin of an aircraft; a light transmissive forward facing light emission surface; and an air deflection zone, which is shaped to direct a portion of an impinging air stream (A) along and over the forward facing light emission surface for shielding the forward facing light emission surface from the impinging air stream (A).
F21V 15/01 - Housings, e.g. material or assembling of housing parts
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
29.
Light module for an elongated interior aircraft light, elongated interior aircraft light, and method of assembling an elongated interior aircraft light
A light module for an elongated interior aircraft light comprises a plurality of light sources, which are configured for emitting light of different colors and which are arranged next to each other, forming an array of light sources extending between a first end and a second end along a longitudinal direction (LD). The plurality of light sources include a first light source, which is arranged at the first end, and a second light source, which is arranged at the second end. The first and second light sources are those from the plurality of light sources that result in a difference of the illuminating properties between the first and second light sources being the smallest difference that is possible for all potential pairs of light sources formed from the plurality of light sources.
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
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
An aircraft beacon light comprises an annular light source support having a plurality of light passing portions; a plurality of light sources, arranged on the annular light source support for a radially outwards emission of light flashes; a light detector for sensing a light output level of at least a subset of the plurality of light sources; and at least one optical element for shaping a beacon light output from light emitted by the plurality of light sources, the at least one optical element having at least one light guiding portion for capturing stray light from at least said subset of the plurality of light sources and for guiding said stray light through the plurality of light passing portions and towards the light detector.
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
F21V 5/04 - Refractors for light sources of lens shape
F21V 23/04 - Arrangement of electric circuit elements in or on lighting devices the elements being switches
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
AIRCRAFT PASSENGER SERVICE UNIT, AIRCRAFT PASSENGER SERVICE UNIT ASSEMBLY, AND METHOD OF DETERMINING SPATIAL POSITIONS AND/OR ORIENTATIONS OF A PLURALITY OF AIRCRAFT PASSENGER SERVICE UNITS
An aircraft passenger service unit, which is configured for being installed in a passenger cabin of an aircraft. The unit includes at least two near field communication interfaces, wherein each of the at least two near field communication interfaces is configured for a wireless exchange of messages with a corresponding near field communication interface of a neighboring aircraft passenger service unit. The messages include information that identifies the aircraft passenger service unit and the near field communication interface sending the respective message.
H04B 5/00 - Near-field transmission systems, e.g. inductive or capacitive transmission systems
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
G01S 1/68 - Marker, boundary, call-sign, or like beacons transmitting signals not carrying directional information
G01S 1/04 - Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmittersReceivers co-operating therewith using radio waves Details
G01S 1/70 - Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmittersReceivers co-operating therewith using electromagnetic waves other than radio waves
32.
AIRCRAFT PASSENGER SERVICE UNIT, AIRCRAFT PASSENGER SERVICE UNIT ASSEMBLY, AND METHOD OF ADAPTING AN AIRCRAFT PASSENGER SERVICE UNIT
An aircraft passenger service unit, which is configured for being installed in a passenger cabin of an aircraft, includes a seat detection sensor for determining a position and/or an orientation of at least one passenger seat, which is located in the vicinity of, in particular below, the aircraft passenger service unit.
An aircraft passenger cabin light. The light has: an elongated shape having a longitudinal direction (L) comprises: a cabin wall illumination assembly, which extends along the longitudinal direction (L) of the aircraft passenger cabin light and which is configured for illuminating a portion of a wall of an aircraft passenger cabin; and a plurality of personal reading light units for providing personal reading light illumination to passengers. The plurality of personal reading light units are arranged in an array extending along the longitudinal direction (L) of the aircraft passenger cabin light Said array is arranged along the cabin wall illumination assembly.
An aircraft exterior anti-collision light system includes a plurality of anti-collision lights and a bus, wherein each of the plurality of anti-collision lights is coupled to the bus. Each of the plurality of anti-collision lights comprises at least one light source and is configured to emit a sequence of light flashes (R, W). Each of the plurality of anti-collision lights is configured to carry out an initialization routine in response to an activation command. Each of the plurality of anti-collision lights is configured to transmit an activation status message on the bus, after the initialization routine has been carried out. Each of the plurality of anti-collision lights is configured to listen on the bus for activation status messages and to log activation status messages received on the bus. Each of the plurality of anti-collision lights is configured to set a timing of (R, W) depending on the activation status messages.
An aircraft overhead passenger service unit comprises a plurality of oxygen masks for supplying oxygen to aircraft passengers in an emergency situation; and at least two different oxygen mask storage portions, which are spaced apart from each other in a longitudinal direction (L). The plurality of oxygen masks are stored in the at least two different oxygen mask storage portions. The aircraft overhead passenger service unit further comprises an oxygen mask controller, which is switchable between at least two different configurations. The at least two different oxygen mask storage portions are individually associated with the at least two different configurations, with each of the at least two different configurations effecting a release of only the oxygen masks of the associated oxygen mask storage portion in the emergency situation.
An aircraft passenger reading light, which is operable in at least two predetermined configurations, comprises: a light source; an optical element; and an actuation mechanism, which is configured to modify a distance between the light source and the optical element. The distance (D) between the light source and the optical element differs in the at least two predetermined configurations and a spatial extension of the illumination, which results from the light output of the light source and the optical element, differs in the at least two predetermined configurations.
An aircraft passenger reading light comprises at least one reading light source, which is arranged for emitting visible light in a reading light emission direction; and at least one infrared light source, which is arranged for emitting infrared light in an infrared light emission direction. The infrared light emission direction is inclined with respect to the reading light emission direction.
B60Q 3/60 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors characterised by optical aspects
B65D 47/08 - Closures with discharging devices other than pumps with pouring spouts or tubesClosures with discharging devices other than pumps with discharge nozzles or passages having articulated or hinged closures
An aircraft light comprises a support board; a light source, arranged on the support board; a first optical element, which is at least partially light transmissive, which is arranged over the light source, and which is fixed to the support board; and a second optical element, which is at least partially light transmissive, wherein the first optical element is interposed between the light source and the second optical element. The first optical element has a first engagement portion and the second optical element has a second engagement portion. The first engagement portion and the second engagement portion establish a positive fit between the first optical element and the second optical element. At least a portion of light, which is emitted by the light source in operation, passes through the first optical element and through the second optical element.
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
B60Q 1/26 - 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
B64D 45/08 - Landing aidsSafety measures to prevent collision with earth's surface optical
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
F21V 17/16 - 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 by deformation of parts of the lighting deviceSnap action mounting
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
39.
Aircraft navigation light and aircraft comprising the same
An aircraft navigation light, configured to be usable as any of a left forward navigation light, a right forward navigation light, and a tail navigation light of an aircraft, comprises a common support plate which is substantially vertical in the aircraft frame of reference; a first light source arranged on the common support plate for emitting red light; a second light source arranged on the common support plate for emitting green light; a third light source arranged on the common support plate for emitting white light; a driving circuit coupled to the first light source, the second light source and the third light source and configured to supply power to a selected one of the first light source, the second light source, and the third light source; and a blocking element arranged to limit the light output of the aircraft navigation light to one lateral side.
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
B60Q 1/26 - 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
40.
Aircraft light with support board and kinematic coupling fixture and aircraft comprising the same
An aircraft light includes a support board; a light source, arranged on the support board; an optical element, arranged over the light source; and a kinematic coupling fixture, establishing a fixed position of the optical element with respect to the support board.
An aircraft light includes a support board and a supporting profile. The support board supports at least one electric light source, in particular at least one LED. The support board has two lateral edges, which extend in a longitudinal direction of the support board and which are spaced apart from each other in a transverse direction (T) of the support board. The supporting profile comprises a receiving space for receiving and supporting the support board. The receiving space is defined by a base, extending in a longitudinal direction (L) of the supporting profile and in a transverse direction (T) of the supporting profile, and two opposing side walls protruding from the base. The supporting profile further comprises two undercut sections, forming opposing slots in the two opposing side walls that are dimensioned for accommodating a lateral edge of the support board, respectively.
An aircraft beacon light includes a light source carrier, wherein the light source carrier comprises a plurality of connection fields, with the plurality of connection fields forming at least two polygonal connection structures on the light source carrier. The beacon also includes a plurality of LED modules, with the plurality of LED modules being arranged along a particular one of the at least two polygonal connection structures and with each of the plurality of LED modules being coupled to a respective connection field of said particular one of the at least two polygonal connection structures.
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
F21V 3/02 - GlobesBowlsCover glasses characterised by the shape
F21V 17/18 - Latch-type fastening, e.g. with rotary action
F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
43.
INTERIOR AIRCRAFT LIGHTING DEVICE, AIRCRAFT COMPRISING AN INTERIOR AIRCRAFT LIGHTING DEVICE AND METHOD OF STARTING AN INTERIOR AIRCRAFT LIGHTING DEVICE
An interior aircraft lighting device includes at least two discharge light modules, including at least one first discharge light module and at least one second discharge light module, wherein each discharge light module contains at least one excitable gas, which emits electromagnetic radiation pursuant to electric excitation The device also includes multiple electrodes, wherein at least one pair of electrodes is assigned to each discharge light module for applying an electric field to the at least one excitable gas within the respective discharge light module. The two electrodes of each pair of electrodes are spaced apart from each other along a longitudinal direction (A) of the respective discharge light module. The pairs of electrodes include at least one first pair of electrodes assigned to the at least one first discharge light module, and at least one second pair of electrodes assigned to the at least one second discharge light module.
Aircraft headlight includes at least one light source; and a light transmissive cover, at least partially covering the at least one light source. The light transmissive cover includes a first layer made of a first material; a second layer made of a second material, which differs from the first material; and at least one electric heating wire for heating the light transmissive cover by passing an electric current through the electric heating wire. The at least one electric heating wire is embedded into the first layer.
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
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
F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
45.
Aircraft headlight, aircraft comprising an aircraft headlight, and method of operating an aircraft headlight
An aircraft headlight includes at least one visible light source for emitting a headlight light output; a light transmissive cover, at least partially covering the at least one visible light source; and at least one infrared emitter for emitting infrared radiation. At least 90% of radiation energy, comprised in the infrared radiation emitted by the at least infrared emitter, is emitted within a predefined wavelength range; and the light transmissive cover allows at least 25%, in particular at least 30%, more particularly at least 45%, of the radiation energy, which is emitted within the predefined wavelength range, to pass through the light transmissive cover.
An exterior aircraft light includes a mounting board, a light source arranged on the mounting board and a lens arranged over the light source. The lens includes a first lens portion on a first side of a cross-sectional center plane, which is orthogonal to the mounting board and which runs through the light source, and a second lens portion on a second side of the cross-sectional center plane. The light also includes a reflector, arranged to reflect light, emitted by the light source into the first lens portion, towards the second lens portion, wherein the lens fully encloses the light source and the reflector.
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
F21S 43/40 - Signalling devices specially adapted for vehicle exteriors, e.g. brake lamps, direction indicator lights or reversing lights characterised by the combination of reflectors and refractors
A system for providing and monitoring UV illumination in an interior of an aircraft includes at least one switchable UV light source; a light detector, responsive to visible light and UV light and configured for providing sensor outputs regarding detected light; and a controller for monitoring an operational status of the at least one switchable UV light source. The controller is configured to determine the operational status of the at least one switchable UV light source by comparing a first sensor output, provided by the light detector when the at least one switchable UV light source is activated, with a second sensor output, provided by the light detector when the at least one switchable UV light source is deactivated.
An autonomous search light system for being mounted to an aircraft includes a search light for emitting an adjustable light output; an RF receiver with at least two RF antennas for receiving RF signals emitted by an RF transmitter; and a controller for determining a position of the RF transmitter in relation to the search light from the received RF signals and for controlling the search light based on the determined position of the RF transmitter.
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 47/02 - Arrangements or adaptations of signal or lighting devices
F21S 8/00 - Lighting devices intended for fixed installation
G01S 5/02 - Position-fixing by co-ordinating two or more direction or position-line determinationsPosition-fixing by co-ordinating two or more distance determinations using radio waves
G11B 7/09 - Disposition or mounting of heads or light sources relatively to record carriers with provision for moving the light beam or focus plane for the purpose of maintaining alignment of the light beam relative to the record carrier during transducing operation, e.g. to compensate for surface irregularities of the latter or for track following
49.
Aircraft beacon light, aircraft comprising an aircraft beacon light, and method of determining a health status of an aircraft beacon light
An aircraft beacon light with integrated health monitoring comprises an annular arrangement of light sources, which are configured for repeatedly emitting beacon light flashes; a light detection sensor surrounded by the annular arrangement of light sources; and at least one reflective portion arranged to reflect light emitted by the annular arrangement of light sources onto the light detection sensor.
H05B 45/50 - 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
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
An aircraft anti-collision light includes a first group of light sources arranged in a first annular configuration around an axis (A) and a second group of light sources arranged in a second annular configuration. The first group of light sources is surrounded by the second group of light sources. The light also has a first lens structure, which is configured for generating a first light output from light emitted by the first group of light sources, a second lens structure, which is configured for generating a second light output from light emitted by the second group of light sources, and a light transmissive cover, which is arranged over the first lens structure and the second lens structure and which passes the first light output and the second light output for emitting a total light output.
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 113/10 - Combination of light sources of different colours
An aircraft passenger service unit includes infrared sensor configured for detecting infrared radiation and for providing a corresponding sensor output, and a controller, which is configured for receiving and evaluating the sensor output provided by the infrared sensor. The infrared sensor is an infrared sensor array configured for detecting infrared radiation emitted within a plurality of spatial sectors covering a detection area below the aircraft passenger service unit; and the infrared sensor array is configured for detecting the infrared radiation individually for each spatial sector and for providing individual sensor signals for the plurality of spatial sectors. The infrared sensor array is configured such that each passenger seat arranged within the detection area is covered by at least two of the plurality of spatial sectors, respectively; and the controller is configured for determining a passenger seating position within a passenger seat from the individual sensor signals.
An electric aircraft emergency power supply module includes at least one electric power cell for storing and supplying electric energy and a controller for controlling charging and discharging of the at least one electric power cell and for determining a charging level of the at least one electric power cell. The controller includes a simulator, which is configured for simulating an electric behavior of at least one temperature sensitive element as a function of the charging level of the at least one electric power cell.
An exterior aircraft light that can be used on an aircraft includes a dome-shaped light transmissive cover, a light emission assembly, and an interface assembly. The light emission assembly comprises a light emission tower portion, having a cover-facing end and an opposite aircraft-facing end and having a hollow channel extending between the aircraft-facing end and the cover-facing end, a platform portion, and at least one light source and at least one optical element, arranged on the platform portion. The interface assembly extends through the hollow channel of the light emission tower portion and comprises an elevated base, which is configured for mechanically supporting and electrically connecting an electric component, the electric component being at least one of a data reception component, a data transmission component, and a data generation component. The interface assembly further comprises at least one signal line, which extends from the elevated base through the interface assembly.
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 23/00 - Arrangement of electric circuit elements in or on lighting devices
F21V 23/04 - Arrangement of electric circuit elements in or on lighting devices the elements being switches
F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
55.
Method of determining operating conditions of an exterior aircraft light, exterior aircraft light, and method of calibrating an exterior aircraft light
min) for detecting erosion of an optical component of the exterior aircraft light, for detecting the presence of ambient light and/or for detecting the presence of fog and/or clouds in front of the exterior aircraft light.
A method of assigning a passenger to a lavatory within an aircraft passenger cabin, wherein the aircraft passenger cabin comprises at least two lavatories, each having a waiting queue, and wherein the aircraft passenger cabin is divided into at least two spatial zones, includes: receiving a lavatory assignment request from a passenger; based on a seat location of said passenger, determining a particular spatial zone of the aircraft passenger cabin which includes the seat location of said passenger; and based on the particular spatial zone, adding the passenger to the waiting queue of a particular lavatory, associated with the particular spatial zone. The configuration of the at least two spatial zones is variable and it is based on a plurality of zone configuration parameters including a queue length of each of the waiting queues of the at least two lavatories.
An aircraft passenger reading light comprises at least one reading light source, which is arranged for emitting visible light in a reading light emission direction; and at least one infrared light source, which is arranged for emitting infrared light in an infrared light emission direction. The infrared light emission direction is inclined with respect to the reading light emission direction.
B60Q 3/60 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors characterised by optical aspects
B65D 47/08 - Closures with discharging devices other than pumps with pouring spouts or tubesClosures with discharging devices other than pumps with discharge nozzles or passages having articulated or hinged closures
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