An emergency lighting system is disclosed herein. The emergency lighting system includes an interior emergency light disposed adjacent an exit door and configured to illuminate the exit door, a plurality of floor lights disposed in a row on a floor, the plurality of floor lights configured to illuminate an aisle, wherein each floor light of the plurality of floor lights is configured to be controlled individually and separately from the other plurality of floor lights, and a controller operatively coupled to the interior emergency light and the plurality of floor lights and configured to activate the interior emergency light in response to an emergency and to activate each of the plurality of floor lights to indicate a direction to the exit door.
A system for filtering a precipitate from a chemical solvent is disclosed herein. The system includes a first pipe segment configured to transport a chemical solvent having a composition dissolved therein, a first ultraviolet light disposed adjacent the first pipe segment and configured to irradiate the chemical solvent and the composition inside the first pipe segment, wherein the composition precipitates from the chemical solvent forming a plurality of particles in response to the first ultraviolet light, a first filter having a first inlet and a first outlet and configured to remove a first portion of the plurality of particles from the chemical solvent, wherein the first inlet is coupled to the first pipe segment, and a second pipe segment coupled to the first outlet and configured to transport the chemical solvent.
B01D 29/56 - Filters with filtering elements stationary during filtration, e.g. pressure or suction filters, not covered by groups Filtering elements therefor with multiple filtering elements, characterised by their mutual disposition in series connection
3.
SYSTEMS AND METHODS FOR INTEGRATION OF ELECTRONIC CIRCUIT SYSTEMS INTO AN AIRCRAFT STRUCTURE
A method for manufacturing an aircraft structure includes additively manufacturing a body portion defining a first cavity and a second cavity. The method further includes disposing electronic components in the first and second cavities. The method further includes additively manufacturing a pathway layer over the electronic components, the pathway layer defines a channel extending between and to the first electronic component and the second electronic component. The method further includes additively manufacturing a conductive pathway in the channel to extend between and to the first electronic component and the second electronic component, whereby the first electronic component is electrically coupled to the second electronic component.
H05K 3/12 - Apparatus or processes for manufacturing printed circuits in which conductive material is applied to the insulating support in such a manner as to form the desired conductive pattern using printing techniques to apply the conductive material
H05K 3/40 - Forming printed elements for providing electric connections to or between printed circuits
4.
System and method having a switching converter and self-switched charge pump configuration
A system for controlling power provided to an electronic device is disclosed herein. The system includes a switching direct current (DC) power source configured to provide an input voltage at a first frequency, a forward converter coupled to the switching DC power source, wherein the forward converter outputs a first voltage and a second voltage, a frequency multiplier coupled to the forward converter and configured to receive the first voltage as an input, a switch coupled to the frequency multiplier and configured to be driven by the frequency multiplier, wherein the switch outputs a fourth voltage, and a voltage multiplier coupled to the switch and configured to be driven by the switch, wherein the voltage multiplier receives the second voltage and outputs a fifth voltage that is greater than the second voltage.
H02M 3/07 - Conversion of DC power input into DC power output without intermediate conversion into AC by static converters using resistors or capacitors, e.g. potential divider using capacitors charged and discharged alternately by semiconductor devices with control electrode
H02M 3/158 - Conversion of DC power input into DC power output without intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators including plural semiconductor devices as final control devices for a single load
A passenger service unit including an ion emitter is disclosed herein. The passenger service unit includes an air outlet assembly, a control unit electronically coupled to the air distribution box, an air gasper assembly coupled to the air distribution box, and an ion emitter coupled to the air gasper assembly and electronically coupled to the control unit, wherein the ion emitter is configured to be controlled by the control unit.
A lighting system and assembly comprising a controller in operable communication with a light unit. The controller is configured to apply a lighting condition using the light unit for a target light color below an upper level of NVIS radiance while controlling a Melanopic-Photopic (M/P) ratio associated with the target light color, and also determine a color mixing for producing NVIS Green A light and NVIS white light for a plurality of levels of NVIS radiance which are less than a maximum NVIS radiance level for a set of M/P ratio values at an upper allowable limit and a set of M/P ratio values at a lower limit.
An extended reality system for generating real-time synthetic imagery during a flight of an aircraft. The system is connectable to a local terrain database via a data network while the aircraft is on the ground and includes: a terrain subset database configured to store a subset of terrain data from the local terrain database; a position database configured to receive a real-time position and orientation of the aircraft during flight; an image generator configured to generate one or more real-time synthetic images of one or more view points from and/or of the aircraft based on the subset of terrain data and the real-time position and orientation of the aircraft; and an encoder 10 configured to convert the one or more real-time synthetic images into one or more media streams. The media streams are configured to be transmitted to one or more display devices via a wireless network.
A fluid removal assembly for an aircraft light is provided. The fluid removal assembly includes a condensate removal valve including a housing; a set of helical compression springs; and a stem disposed within the housing. The stem is configured to translate in a first direction responsive to the aircraft being pressurized and a first force, from the pressurization, forcing the stem to translate in the first direction; and translate in a second direction opposite the first direction responsive to the aircraft being depressurized and a second force from the set of helical compression springs forcing the stem to translate in the second direction. The condensate removal valve is configured to: responsive to an aircraft being depressurized, drain a fluid from one or more components of the aircraft light, the aircraft light being installed in the aircraft; and responsive to the aircraft being pressurized, maintain a pressure within the aircraft.
A system for controlling in-flight services using gestures is disclosed. The system comprises: a gesture detection device; an actuator; and a controller. The controller is configured to: receive a detected free space gesture from the gesture detection device; compare the detected free space gesture to a plurality of identified free space gestures; responsive to identifying a free space gesture from the plurality of identified free space gestures, identify an associated in-flight service based on the identified free space gesture; and responsive to identifying the associated in-flight service, send a first command to the actuator to perform the associated in-flight service.
A system for displaying an artificial horizon in an enclosed space. The system includes a first plurality of visual effect sources located in the enclosed space and configured to generate a first visual effect of the artificial horizon consistent with an orientation detected by an orientation sensor. The system further includes a second plurality of visual effect sources separate from the first plurality of visual effect sources and located in the enclosed space and configured to generate a second visual effect of the artificial horizon different from the first visual effect consistent with the orientation detected by the orientation sensor.
An aircraft light unit is disclosed herein. The aircraft light unit includes a housing having a first side and an opposing second side, a light coupled to the first side of the housing, a circuit board assembly coupled to second side of the housing, a thermoelectric cooler coupled to the circuit board assembly and configured to dissipated heat from the circuit board assembly, and a heat sink disposed over the thermoelectric cooler and configured to dissipate heat from the thermoelectric cooler.
F21S 45/47 - Passive cooling, e.g. using fins, thermal conductive elements or openings
F21V 29/54 - Cooling arrangements using thermoelectric means, e.g. Peltier elements
G05B 19/4155 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by programme execution, i.e. part programme or machine function execution, e.g. selection of a programme
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
A light assembly includes a mounting bracket, a light coupled to the mounting bracket, a guide sensor coupled to the mounting bracket, a movement mechanism coupled to the mounting bracket, and a controller operably coupled to the light assembly. The controller is configured to receive data from the guide sensor and command actuation of the movement mechanism in response to the data received from the guide sensor.
A de-icing light assembly may comprise: a housing; a plurality of lights coupled to the housing; a lens assembly coupled to the housing, the lens assembly comprising: a lens material; an indium tin oxide (ITO) film disposed on the lens material; and a silicon oxide coating disposed on the ITO film.
Systems and methods for deicing an aircraft landing light may include a metal mesh conductor coupled to a lens of a landing light. The systems and methods may include a power supply, a temperature sensor, a deicing control unit, an aircraft light having a lens, and a mesh coupled to the lens. The temperature sensor may be a microwave resonator sensor configured to sense the temperature of the landing light and send signals to the deicing control unit. The signals may be configured to instruct the deicing control unit to either apply an electric current to the mesh, or cease applying an electric current to the mesh, depending on the landing light temperatures. The deicing control unit may receive landing pulses from a flight control system. The pulses may indicate that the aircraft is landing or has landed.
A nonlinear converter may comprise: alternating layers of a dielectric material and a metal material; a first refractive index of the nonlinear converter for a first wavelength (i.e., input wavelength or pump wavelength) between 207 nm and 237 nm, the first refractive index being less than 0.5, the first refractive index corresponding to metal fill ratio; and a second refractive index of the nonlinear converter for a second wavelength (i.e., output wavelength or SHG wavelength), the second wavelength being approximately double the first wavelength, the second refractive index corresponding to the metal fill ratio.
A light system may comprise: a seat back housing configured to be coupled to a seat in an aircraft; a light assembly coupled to the seat back housing, the light assembly comprising: a main body at least partially disposed in the seatback housing in response to the light assembly being in a stowed state, the main body coupled to a joint and configured to move relative to the joint, and a light coupled to the main body.
A light assembly may comprise: a light array comprising a plurality of light emitting diodes (LEDs), each light emitting diode (LED) configured to emit an electromagnetic radiation having a wavelength, the wavelength of each LED being different, a first LED in the light array configured to emit a first wavelength between 414 nm and 474 nm; and a non-linear optical layer disposed adjacent to the first LED, the nonlinear optical layer configured to output the first wavelength and a second wavelength, the second wavelength being between 207 nm and 237 nm.
An autonomous light system may comprise a reading light assembly, an object detection device; and a controller. The reading light assembly may include a light source and an actuation system. The controller may be operably coupled to the light source and the object detection device. The controller may include an object detection module and may be configured to receive object data from the object detection device, compare the object data against an object database, identify an object based on the comparison of the object data to the object database, send a first command to at least one of the light source and the actuation system.
H05B 47/12 - Controlling the light source in response to determined parameters by determining the presence or movement of objects or living beings by detecting audible sound
F21V 14/02 - Controlling the distribution of the light emitted by adjustment of elements by movement of light sources
H05B 47/125 - Controlling the light source in response to determined parameters by determining the presence or movement of objects or living beings by using cameras
G06V 20/59 - Context or environment of the image inside of a vehicle, e.g. relating to seat occupancy, driver state or inner lighting conditions
G06V 40/18 - Eye characteristics, e.g. of the iris
F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
19.
Sanitization systems and methods with UVC lighting
A sanitization system for an aircraft may comprise: a lighting system disposed in the aircraft cabin, the lighting system including a plurality of sanitization lights, the plurality of sanitization lights configured to emit UV-C radiation; an electrical port in electrical communication with the lighting system; an external power source disposed away from the aircraft; and an electrical cable coupled to the external power source, the electrical cable configured to removably couple to the electrical port to provide electrical power to the plurality of sanitization lights.
An exterior lamp for an aircraft may comprise a housing, a navigation light disposed within the housing, and a brake light disposed within the housing, wherein the brake light is configured to illuminate in response to a brake signal. The exterior lamp may include a controller disposed within the housing, and a tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising receiving a brake signal and illuminating the brake light in response to a brake signal.
Systems and methods for light emitting diodes (LEDs) circuits are provided. Aspects include a set of light emitting diodes (LEDs) arranged in series between a first node and a second node, a power supply coupled to the first node, a first switching element arranged in series between the first node and a third node, wherein the first switching element is in parallel with the set of LEDs, a first charge pump coupled to the third node, a controller configured to operate the first switching element by providing a control voltage for switching the first switching element between an ON and an OFF, wherein the control voltage comprises a switching frequency, and wherein the first charge pump is charged by the power supply responsive to the switching element being in an ON state.
H05B 45/10 - Controlling the intensity of the light
H05B 45/48 - Details of LED load circuits with an active control inside an LED matrix having LEDs organised in strings and incorporating parallel shunting devices
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
22.
Driving light emitting diodes and display apparatus
Systems and methods for operating light emitting diodes (LEDs) circuits are provided. Aspects include a power supply coupled to the first node, a set of light emitting diodes (LEDs) arranged in series between a second node and a third node, a boost converter coupled to the first node and the second node, a first control circuit configured to operate a first switching element to control operation of the boost convertor, wherein the boost convertor outputs a step-up voltage to drive the set of LEDs, and a second control circuit to operate the second switching element to control operation of the set of LEDs, the second switching element coupled to the third node, wherein the set of LEDs are ON responsive to the second switching element being in an ON state.
F21V 23/00 - Arrangement of electric circuit elements in or on lighting devices
F21V 23/02 - Arrangement of electric circuit elements in or on lighting devices the elements being transformers or impedances
H03K 19/20 - Logic circuits, i.e. having at least two inputs acting on one outputInverting circuits characterised by logic function, e.g. AND, OR, NOR, NOT circuits
The present disclosure provides a night vision imaging system (NVIS) lighting system, comprising a frame comprising a first light source, a second light source adjacent to the first light source, a third light source adjacent to the second light source, and a diffuser mounted to the frame and encasing the first light source, the second light source, and the third light source. The first light source may comprise a first dominant wavelength, the second light source may comprise a second dominant wavelength different from the first dominant wavelength, and the third light source may comprise a third dominant wavelength different from the first dominant wavelength and the second dominant wavelength. Light emitted from the first light source, the second light source, and the third light source may be blended to generate a first blended light source comprising a first target output color.
B60Q 3/60 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors characterised by optical aspects
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
F21V 15/01 - Housings, e.g. material or assembling of housing parts
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
F21Y 113/13 - Combination of light sources of different colours comprising an assembly of point-like light sources
A light assembly for use on an aircraft is disclosed herein. The light assembly comprises a reflector assembly, a printed wiring assembly, and a bezel assembly. The bezel assembly may comprise a first worm screw. The first worm screw may be configured to translate at least one of the reflector assembly and the printed wiring assembly in a first direction. The bezel assembly may comprise a second worm screw. The second worm screw may be configured to translate at least one of the reflector assembly and the printed wiring assembly in a second direction.
F21S 41/151 - Light emitting diodes [LED] arranged in one or more lines
F21S 41/143 - Light emitting diodes [LED] the main emission direction of the LED being parallel to the optical axis of the illuminating device
F16H 19/04 - Gearings comprising essentially only toothed gears or friction members and not capable of conveying indefinitely-continuing rotary motion for interconverting rotary motion and reciprocating motion comprising a rack
F21S 41/36 - Combinations of two or more separate reflectors
F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
F21W 104/00 - Exterior vehicle lighting devices for decorative purposes
An aircraft emergency exit door indication system may comprise a first plurality of light sources, a controller, and a first sensor associated with a first exit door. The first sensor feedback signal indicates an availability for egress through the first exit door. The first plurality of light sources is operated by the controller based upon the first sensor feedback signal. The light sources may be lights that already exist in an aircraft such as ceiling wash lights, sidewall wash lights, floor path lights, dome lights, or passenger service unit lights. The system may include a second plurality of light sources logically separated from the first plurality of light sources based upon its location relative to the first exit door and a second exit door.
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
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
G09F 13/04 - Signs, boards, or panels, illuminated from behind the insignia
An aircraft may include a first pair of forward-facing flash position lamps disposed at a first wing tip, the first pair of flash position lamps comprising a first flash position lamp and a second flash position lamp, a second pair of forward-facing flash position lamps disposed at a second wing tip, the second pair of flash position lamps comprising a third flash position lamp and a fourth flash position lamp, and a controller in electronic communication with the first pair of flash position lamps, wherein at least one of the first flash position lamp and the second flash position lamp are configured to flash, while maintaining a combined intensity of the first pair of forward-facing flash position lamps above a desired intensity, to indicate a change in direction of the aircraft.
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
G08B 5/38 - Visible signalling systems, e.g. personal calling systems, remote indication of seats occupied using electric transmissionVisible signalling systems, e.g. personal calling systems, remote indication of seats occupied using electromagnetic transmission using visible light sources using flashing light
An LED light system for an aircraft may comprise a first LED lamp having a first LED array. The first LED array may include at least a first LED and a second LED. A first optical element may be configured to direct light emitted from the first LED in a first beam centered around a first angle and to direct light emitted from the second LED in a second beam centered around a second angle. The LED light system may further comprise a second LED lamp having a second LED array. The second LED array may include at least a third LED and a fourth LED. A second optical element may be configured to direct light emitted from the third LED in a third beam centered around the first angle and to direct light emitted from the fourth LED in a fourth beam centered around the second angle.
A dual mode light assembly for a forward position light of an aircraft includes a base, a visible light source mounted to the base that is configured to emit visible light, a covert light source mounted to the base that is configured to emit covert light, and a light shield mounted to the base. The light shield is configured to restrict transmission of the visible light to a visible light pattern and to restrict transmission of the covert light to a covert light pattern.
An LED light system for an aircraft may comprise a first LED lamp having a first LED array. The first LED array may include at least a first LED and a second LED. A first optical element may be configured to direct light emitted from the first LED in a first beam centered around a first angle and to direct light emitted from the second LED in a second beam centered around a second angle. The LED light system may further comprise a second LED lamp having a second LED array. The second LED array may include at least a third LED and a fourth LED. A second optical element may be configured to direct light emitted from the third LED in a third beam centered around the first angle and to direct light emitted from the fourth LED in a fourth beam centered around the second angle.
A device for forming a dynamic image on an aircraft sign includes a plurality of light sources, an input power line, a first timer and a second timer both connected to an enable input and a plurality of delay circuits each connected to a different one of the light sources. The system also includes a counter having a plurality of counter outputs, the counter receiving a counting pulse from the first timer in a dynamic mode of operation and disable signal from the second timer after expiration of a preset time, the expiration of the preset time causing the device to transfer from the dynamic mode to a static mode where each of the plurality of light sources are simultaneously illuminated.
G08B 5/36 - Visible signalling systems, e.g. personal calling systems, remote indication of seats occupied using electric transmissionVisible signalling systems, e.g. personal calling systems, remote indication of seats occupied using electromagnetic transmission using visible light sources
G09F 13/22 - Illuminated signsLuminous advertising with luminescent surfaces or parts electroluminescent
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
A dual mode light assembly for a forward position light of an aircraft includes a base, a visible light source mounted to the base that is configured to emit visible light, a covert light source mounted to the base that is configured to emit covert light, and a light shield mounted to the base. The light shield is configured to restrict transmission of the visible light to a visible light pattern and to restrict transmission of the covert light to a covert light pattern.
A light source includes a circular light element having a light source diameter, and a reflector disposed at least partially within the circular light element, the reflector having a first end with a first diameter and a second end with a second diameter, wherein the first diameter is less than the light source diameter and the second diameter is larger than the light source diameter, the second end having a plurality of slits.
A light source includes a circular light element having a light source diameter, and a reflector disposed at least partially within the circular light element, the reflector having a first end with a first diameter and a second end with a second diameter, wherein the first diameter is less than the light source diameter and the second diameter is larger than the light source diameter, the second end having a plurality of slits.
A dual mode light includes a housing, at least one first light emitter disposed in the housing, a plurality of second light emitters each disposed in the housing an emitter distance from the at least one first light emitter, a first shield disposed in the housing a first shield distance from the at least one first light emitter, wherein the first shield distance is less than the emitter distance, and a second shield disposed in the housing a second shield distance around the plurality of second light emitters.
A dual mode light includes a housing, at least one first light emitter disposed in the housing, a plurality of second light emitters each disposed in the housing an emitter distance from the at least one first light emitter, a first shield disposed in the housing a first shield distance from the at least one first light emitter, wherein the first shield distance is less than the emitter distance, and a second shield disposed in the housing a second shield distance around the plurality of second light emitters.
A device for projecting an image on a projector module screen, comprising an interchangeable disc including at least one image disposed thereon and a light source for illuminating the at least one image. The device further includes a lens for receiving the at least one image from the interchangeable disc and passing the image to the projector module screen, wherein the projector module screen displays the image and a projector module housing enclosing the interchangeable disc, the light source, and the lens.
A landing light system and steering method and computer readable medium is provided. A landing light system includes a camera, a controller, and a landing light. A tangible, non-transitory memory may have instructions for controlling a landing light. The controller may perform operations including receiving a first image at a first time from the camera, receiving a second image at a second time from the camera, estimating a focus of expansion between the first image and the second image, and aiming the landing light based on the focus of expansion.
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraftCombined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
B64D 47/04 - Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
A system and method for estimating a distance between an aircraft and an object is disclosed. An exterior light of the aircraft transmit a test light signal and a parameter the transmitted test light signal is measured. A sensor receives a reflection of the test light signal from the object and the parameter is measured for the reflection test signal. The distance between the aircraft and the object is estimated using the parameter of the reflection and the parameter of the test light signal. The exterior light is generally a light that is built into the aircraft during aircraft construction while the sensor is retrofitted onto the aircraft.
In a lighting system that emits light of a color within a color specification, the color is controlled by adding light from a single color-correcting light emitting device (light- emitting device) to a primary light-emitting device. In an illustrative embodiment, a color- detecting module can sense the color of the combined light emitted from both the primary and the color- correcting light-emitting devices. The color-control system can generate an amplitude control signal based on a signal indicative of the color sensed by the color-detecting module. A color range of the combined light of the primary and the color-correcting light-emitting devices can intersect a domain of the predetermined color specification, as the generated amplitude control signal spans the domain. Using a single color-correcting light-emitting device to maintain a lighting system's emitted color within a predetermined color specification can advantageously reduce system complexity.
G08B 5/36 - Visible signalling systems, e.g. personal calling systems, remote indication of seats occupied using electric transmissionVisible signalling systems, e.g. personal calling systems, remote indication of seats occupied using electromagnetic transmission using visible light sources
H05B 47/155 - Coordinated control of two or more light sources
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
40.
Lighting-system color-shift detection and correction
In a lighting system that emits light of a color within a color specification, the color is controlled by adding light from a single color-correcting light emitting device (light-emitting device) to a primary light-emitting device. In an illustrative embodiment, a color-detecting module can sense the color of the combined light emitted from both the primary and the color-correcting light-emitting devices. The color-control system can generate an amplitude control signal based on a signal indicative of the color sensed by the color-detecting module. A color range of the combined light of the primary and the color-correcting light-emitting devices can intersect a domain of the predetermined color specification, as the generated amplitude control signal spans the domain. Using a single color-correcting light-emitting device to maintain a lighting system's emitted color within a predetermined color specification can advantageously reduce system complexity.
Light systems having an array of paired visible-light and infrared-light elements, each pair arranged such that a body of each visible-light element obstructs infrared-light emitted from its paired infrared-light element. A lens might be provided to cover the array of paired light elements.
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
F21S 10/02 - Lighting devices or systems producing a varying lighting effect changing colours
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
B64D 7/00 - Arrangement of military equipment, e.g. armaments, armament accessories or military shielding, in aircraftAdaptations of armament mountings for aircraft
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
42.
Method of color mixing for an aviation anti-collision light
A dual-color aviation Anti Collision Light (ACL) has a first set of LEDs that emit a substantially white beam of light and a second set of LEDs that emit a substantially red beam of light. The ACL can be operated in a first mode in which the red LEDs are excited by themselves so that the ACL produces a red beam of light In a second mode, the white LEDs and the red LEDs are excited simultaneously to produce a white beam of light having a chromaticity within the definition of Aviation White. Operating the red LEDs in the white mode has two synergistic effects. First, the red LEDs augment the luminous output of the white LEDs so that fewer white LEDs are required, thus saving cost and space. Second, the red LEDs shift the chromaticity of total light output toward the red region. This has the effect of compensating for the tendency of the white LEDs to become greener with age.
A wireless communications system suitable for use within an aircraft, such as a part of a wireless emergency lighting system (WELS) is provided. In an aircraft, EXIT signs are located throughout the interior of the aircraft, including the ceiling (general illumination), seats (floor proximity) and EXIT doors (locator/identifier). A wireless communications system uses an integrated lens antenna system that takes advantage of the quantity and location of emergency lights such that any given light will have a direct radio frequency (RF) path to several other lights. A virtual network can be created such that if the path between any two lights becomes disrupted, alternate paths will be constructed under software control.
patents
