50results about "Aircraft lights" patented technology

The present disclosure provides a method for site management that includes launching, from a mobile drone base unit, a drone including a sensor package and an illumination source; tethering, by a tether coupling the drone to the mobile drone base unit, the drone to provide power and maintain communications between the drone and the mobile drone base unit; receiving, from the sensor package of the drone, data related to a construction site; comparing the received data related to the construction site to blueprint data related to the construction site; and in response to identifying a deviation between the received data and the blueprint data, moving the mobile drone base unit to a position allowing the drone to highlight the deviation.

An aircraft reading light (2) with a color-tunable reading light output (3) comprises a white light source (12) for emitting white light; a colored light source (14) for emitting colored light; and an optical element (181), which is arranged for directing colored light that is emitted by the colored light source (14) onto the white light source (12) for being diffusely reflected at the white light source (12). The colored light source (14) is controllable independently from the white light source (12).

In an example embodiment, a drone-based system comprises: a base station, wherein the base station is configured to provide drone control and power; a drone; a tether connecting the base station to the drone and configured to provide the drone with the power from the base station; and a lighting system, operably attached to the drone via the tether, configured to generate illumination of a ground area, wherein the illumination of the ground area is controllable by modifying least one of an intensity of the illumination and a height of the drone above the ground area.

A mechanically sealed LED assembly is designed for enhanced ingress protection in UAV night flight modules. The assembly includes multiple LEDs enclosed within sealed cavities to prevent dust and water ingress, ensuring safe operation in various environmental conditions. An ingress protection stack, comprising an LED base layer, seal components, a baffle, and cover glass, provides additional protection. The seal components are compressed against the LED base layer by the baffle, enhancing the assembly's durability and performance. This design allows for enhanced optical power output while maintaining protection from environmental elements.

To provide a runway-embedded flash device that is light-weight, has a long life and high effective luminous intensity, can switch luminous intensity, has small power consumption, and can be placed on the ground surface with its bottom facing down without requiring a stand or the like.SOLUTION: A runway-embedded flash device comprises a cylindrical body 10, a ceiling member 11, a light guide member 12, an LED flashlight source 13, and a bottom cover member 16. The ceiling member is arranged on an upper opening part of the cylindrical body 10 in a state of being exposed to a runway surface. The ceiling member 11 is provided with a window for flashlight irradiation. The light guide member 12 is arranged at the window for flashlight irradiation. The LED flashlight source 13 is arranged in the cylindrical body 10 in a state of being capable of emitting flashlight toward the light guide member 12 arranged at a window for flashlight source. The light guide member 12 allows the flashlight emitted from the LED flashlight source 13 to be emitted from the window for flashlight irradiation to the outside. The bottom cover member 16 is arranged in a state of being capable of closing a lower opening part of the cylindrical body 10. The bottom cover member 16 has a support part 17 protruding from an external surface of the bottom cover member 16 on a side opposite the cylindrical body 10 side.SELECTED DRAWING: Figure 1

A light unit executes up to three different functions (cabin area illumination, individual / dedicated / decorative illumination and emergency illumination) and an emergency illuminated sign unit, each one with an internal controller and a rechargeable capacitor. An example non-limiting embodiment also provides a cabin light system and an emergency lighting system, where each illumination unit (light source or illuminated sign) is as described above.

An aircraft power system for providing regulated voltage and regulating power fluctuations in a tethered aircraft includes a plurality of light-emitting diodes (LEDs) onboard an aircraft having at least one propulsion unit. At least one electrical circuit is onboard the aircraft. The at least one electrical circuit includes a current-amplifying regulator in parallel with a speed controller of the at least one propulsion unit, the current-amplifying regulator in parallel with the speed controller providing the regulated voltage to the speed controller. A tether is connected between the aircraft and a power source located remotely from the aircraft. Power is transmitted via the tether to the aircraft and at least a portion of the plurality of LEDs.

An aircraft tail light (2) for being installed adjacent a hot gas exhaust (8) of an aircraft (100) comprises: at least one light source (10) for generating a light output of the aircraft tail light (2) and a heat transfer structure (14). The at least one light source (10) is arranged in an aircraft exterior portion (3) of the aircraft tail light (2). The heat transfer structure (14) comprises a heat receiving portion (14a), thermally coupled with the at least one light source (10) for absorbing heat (H) from the at least one light source (10), and a heat dispensing portion (14b) for dispensing heat (H) from the heat transfer structure (14). The heat transfer structure (14) extends from the aircraft exterior portion (3) of the aircraft tail light (2) to an aircraft interior portion (5) of the aircraft tail light (2). The heat receiving portion (14a) is arranged in the aircraft exterior portion (3) of the aircraft tail light (2) and the heat dispensing portion (14b) is arranged in the aircraft interior portion (5) of the aircraft tail light (2).

Disclosed in an example embodiment herein is an airfield luminaire, comprising a housing, a light source in an interior of the housing, a sensor for sensing a condition associated with the housing, and control logic comprising a processor coupled with the light source and the sensor. The control logic is operable to obtain data from the sensor and determine a status of the airfield luminaire. In another example embodiment, a controller is operable to receive data representative of sensor data from the plurality of airfield lighting fixtures and determine the status of a selected one of the plurality if lighting fixtures based on the sensor data. In yet another example embodiment control logic that comprises a processor is operable to determine the present light output of a LED based on aging rate and amount of time the LED is operated at a plurality of temperatures.

This invention provides a new runway-embedded flashing device that is lightweight, has a long lifespan, high effective luminous intensity, allows for luminous intensity switching, consumes little power, and can be placed on the ground with its base facing downwards. [Solution] The runway embedded flashing device 1 of the present invention includes a cylindrical body 10, a ceiling member 11, a light guide member 12, an LED flashing light source 13, and a bottom cover member 16. The cylindrical body 10 is embeddable in the runway, the ceiling member 11 is positioned at the upper opening of the cylindrical body 10, and the ceiling member 11 is provided with a flashing light irradiation window, the light guide member 12 is positioned at the flashing light irradiation window, the LED flashing light source 13 is positioned inside the cylindrical body 10 in a manner that allows flashing light to be irradiated toward the light guide member 12 positioned at the flashing light irradiation window, the flashing light irradiated from the LED flashing light source 13 by the light guide member 12 can be irradiated toward the outside through the flashing light irradiation window, and the bottom cover member 16 is positioned in a manner that allows closing the lower opening of the cylindrical body 10.

Innovative peripheral bar assembly for a transportation vehicle is provided. One method includes transmitting, by a processor of a seat device of an aircraft coupled to a peripheral bar assembly having a plurality of programmable light sources, one or more commands to the peripheral bar assembly to operate one or more of the light sources; and operating, by the peripheral bar assembly, the one or more light sources, in response to the one or more commands to indicate non-verbal communication associated with the aircraft.

A surface-mounted luminaire (2) for a passenger cabin (4) of a passenger aircraft (6) comprises a layered, planar base carrier (8), one flat side (10a) of which is a light-emitting side (12) and a plurality of LEDs (14) which are arranged planarly on the light-emitting side (12) of the base carrier (8), wherein a plurality of the LEDs (14) are accent LEDs (LA) which, in operation (B), produce colored light of a selectable color and which are planarly distributed over the base carrier (8), wherein at least two of the accent LEDs (LA) are individually adjustable with respect to a color and brightness of the light they produce in operation (B), wherein a plurality of the LEDs (14) are basic LEDs (LG) which, in operation, produce white light and which are planar distributed over the base carrier (8), wherein at least two of the basic LEDs (LG) are only jointly adjustable with respect to the brightness of the light they produce in operation (B).and wherein a large number of the LEDs (14) in operation (B) are white light-producing emergency LEDs (LN) which are distributed over the surface of the base carrier (8), wherein all emergency LEDs (LN) can be supplied with energy independently of the accent LEDs (LA) and base LEDs (LG).

An aerial vehicle electrical power system for use with a tethered aerial vehicle, and related methods are provided. The aerial vehicle electric power system includes a plurality of light-emitting diodes (LEDs) carried by an aerial vehicle. At least one electrical circuit is carried by the aerial vehicle. The at least one electrical circuit has a DC converter electrically in series with at least a portion of the plurality of LEDs. A tether is connected between the aerial vehicle and a power source positioned remote from the aerial vehicle. Electrical power is transmitted to the aerial vehicle and at least a portion of the plurality of LEDs through the tether. The electrical circuit minimizes variances in power supplied to the aerial vehicle and the plurality of LEDs.

The aerial drone system includes a first drone (14), a second drone (14), and an electronic media tether (36) coupled to the first drone and the second drone, wherein the first drone (14) includes a first drone body and a first propeller system configured to propel the first drone through the air, and the second drone (14) includes a second drone body and a second propeller system configured to propel the second drone through the air, and the electronic media tether (36) includes a plurality of light-emitting diodes (LEDs) (37) and is configured to transmit power to the plurality of LEDs (37).

An aircraft tail navigation light (106c) comprises: a navigation lighting assembly (4) for emitting a regular navigation light output; and an orientation lighting assembly (6) for emitting an orientation light output. The aircraft tail navigation light (106c) is switchable between emitting the regular navigation light output having a navigation light intensity and emitting the orientation light output having an orientation light intensity, with the navigation light intensity being larger than the orientation light intensity.

An aircraft includes a fuselage and a plurality of light assemblies mounted on the fuselage. Each light assembly includes a housing, a light source, and a lens cover. The light source is mounted within the housing. The lens cover is coupled to the housing and surrounds at least a portion of the light source. The lens cover includes a plurality of retroreflectors. The aircraft may also include a windscreen and a plurality of retroreflectors adjacent the windscreen. The aircraft may also include a plurality of windows at a least one retroreflector adjacent each window.

A tethered UAV providing broad area lighting including a weatherproof drone; an electrically conductive tether; a high voltage power supply; an LED light engine which consumes at least 800 watts of power; an uninterruptible power source; and a voltage isolation stage. The weatherproof drone may or may not include a battery. The weatherproof drone, minus a battery, electrically conductive tether, and LED light engine weigh less than 4.4 pounds. The LED light engine produces 5 footcandles or more over an area greater than 50 feet in diameter.

[Object] To provide a control device which enables a flight vehicle device to obtain a highly precise image.[Solution] Provided is the control device including an illuminating control unit configured to adjust a light amount of an illuminating device according to an inclination of a fuselage of a flight vehicle device that has an imaging device configured to photograph a photographing target and the illuminating device configured to illuminate the photographing target.

To provide a new runway-embedded flashing device that is light-weight, has long life, has high effective luminous intensity, can switch luminous intensity and has less power consumption.SOLUTION: A runway-embedded flash device 1 of the present invention comprises a cylindrical body 10, a ceiling member 11, a light guide member 12, and an LED flash light source 13. The cylindrical body 10 can be embedded in a runway. The ceiling member 11 is arranged on an upper opening part of the cylindrical body 10 in a state where it can be exposed to a runway surface when the cylindrical body 10 is embedded in the runway. The ceiling member 11 is provided with a window for flash light emission. The light guide member 12 is arranged on the window for flash light emission. The LED flash light source 13 is arranged in the cylindrical body 10 in a state where it can emit flash light toward the light guide member 12 arranged on the window for a flash light source. The light guide member 12 allows the flash light emitted from the LED flash light source 13 to be emitted to the outside from the window for flash light emission.SELECTED DRAWING: Figure 1

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.

An aircraft passenger cabin light (2) having an elongated shape having a longitudinal direction (L) comprises: a cabin wall illumination assembly (4), which extends along the longitudinal direction (L) of the aircraft passenger cabin light (2) and which is configured for illuminating a portion of a wall (120) of an aircraft passenger cabin (104); and a plurality of personal reading light units (12a, 12b) for providing personal reading light illumination to passengers. The plurality of personal reading light units (12a, 12b) are arranged in an array extending along the longitudinal direction (L) of the aircraft passenger cabin light (2). Said array is arranged along the cabin wall illumination assembly (4).

To provide a novel runway-embedded flash light device that is lightweight, long in life, high in effective luminous intensity, capable of switching light intensity, small in power consumption, and superior in heat dissipation.SOLUTION: A runway-embedded flash light device 1 includes a cylindrical body 10, a ceiling member 11, a light guide member 12, an LED flash light source 13, and a heat conductive member 17. The cylindrical body 10 can be embedded in a runway 2, the ceiling member 11 is arranged at an upper opening part of the cylindrical body 10 so that it can be exposed to a runway surface, and the light guide member 12 is arranged at a flash light irradiation window. The LED flash light source 13 is so arranged as to irradiate the light guide member 12 arranged at the flash light irradiation window with flash light, the light guide member 12 can emit the flash light, emitted by the LED flash light source 13, to the outside through the flash light irradiation window, and the heat conductive member 17 is arranged in the cylindrical body 10 to come into contact with the LED flash light source 13, at least a part of the other part of the heat conductive member 17 being in contact with the ceiling member 11.SELECTED DRAWING: Figure 1

Innovative peripheral bar assembly for a transportation vehicle is provided. One method includes transmitting, by a processor of a seat device of an aircraft coupled to a peripheral bar assembly having a plurality of programmable light sources, one or more commands to the peripheral bar assembly to operate one or more of the light sources; and operating, by the peripheral bar assembly, the one or more light sources, in response to the one or more commands to indicate non-verbal communication associated with the aircraft.

Aircraft glazing and window arrangement equipped with an improved lighting device. The invention relates to a glazing arrangement (2) for a window (8) extending in a plane (10) and housed in the outer wall (4) of an aircraft (6). It comprises a transparent cover pane (12) in a cover plane (14); an electrically switchable film (16) extending in a dispersion plane (18); and a luminescent film (20) extending, at a distance (D), in a luminescence plane (22) parallel to said plane (18). Several light-emitting diodes (24) are implanted on said film (20), the mutual spacing (A) between said diodes (24) being at least five times their transverse extent (Q). Said arrangement (2) is designed to be positioned in front of the window (8), in the direction of a line of sight (26) perpendicular to the plane (10) thereof, pointing towards a cabin (42) of the aircraft (6).The planes (18, 22, 10) extend in parallel, with film (20) interposed between window (8) and film (16). Window (8) and films (16, 20) are placed in aligned succession along line (26). A window arrangement includes window (8) and the aforementioned glazing arrangement (2). Figure to be published with the abbreviation: Fig. 1.

An aircraft passenger reading light comprises a plurality of pairs of light sources. Each of the plurality of pairs of light sources includes: a first light source for emitting light having a first color, and a second light source for emitting light having a second color, wherein the second color differs from the first color. The aircraft passenger reading light further comprises, for each of the plurality of pairs of light sources: a first optical system for forming a first light output from the light emitted by the first light source, and a second optical system for forming a second light output from the light emitted by the second light source.

An aircraft tail navigation light comprises: a navigation lighting assembly for emitting a regular navigation light output; and an orientation lighting assembly for emitting an orientation light output. The aircraft tail navigation light is switchable between emitting the regular navigation light output having a navigation light intensity and emitting the orientation light output having an orientation light intensity, with the navigation light intensity being larger than the orientation light intensity

A system is provided for illuminating a winglet cap (120) of a winglet (108). The system includes the winglet cap (120), a light source (306), a total internal reflection (TIR) lens (302) positioned in proximity to the light source (306), and a prismatic lens (408) positioned between the light source (306) and the winglet cap (120). In the system, light produced by the light source (306) reflects off a surface of the TIR lens (302) and passes through the prismatic lens (408). In the system, the prismatic lens (408) bends the light and directs the bent light toward an inside surface of the winglet cap (120).

Active standby (33) refers to the method for implementing an obstruction lighting system (2) consisting of n light sources (3), where n is a natural number and n > 1, with identical or similar specifications, placed inside i luminaires (4), where i = 1,...,n, at the top and / or along the height or width of the aviation obstacle (1) that requires marking. The method aims at safer operation, increased reliability, and an extended application field for the system (2), and is achieved through the simultaneous start of the periodic operating cycle of all n fight sources (3), main and auxiliary, in contrast to their serial operation with continuous (9) or periodic (10) light emission under prior art (9, 10, 31). The system (2) can produce either a continuous active light front with afterglow (26, 29) or without afterglow (25), or a periodic active light front, called regular flashing, with afterglow (28) or without afterglow (27), or a periodic active light front, called emergency flashing (36), with or without afterglow. It may also emit a coded message indicating position, emergency status, or communication in general, depending on the conditions and requirements defined by ICAO / FAA regulations and standards for each specific application.

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 (2) comprises: a support element (4), supporting at least one light source (6); an injection molded optical element (8), made of light transmissive silicone rubber; and a layer of light transmissive silicone rubber (12) arranged between at least a portion of the injection molded optical element (8) and at least a portion (4b) of the support element (4). The layer of light transmissive silicone rubber (12) provides adhesion between the injection molded optical element (8) and the support element (4).