92results about "Aircraft lights" patented technology

An aerial lighting system includes: two or more unmanned aerial vehicles (UAVs) each including a corresponding high-powered LED array arranged to illuminate an area beneath the UAVs when the UAVs are airborne; a base station configured to retain the UAVs when not airborne, wherein the base station includes a controller for controlling the UAVs; and a plurality of cables for transferring power and data, including: (i) a first cable detachably coupled between the base station and a first UAV, wherein the first UAV receives power from the base station and communicates with the controller via the first cable, and (ii) a second cable detachably coupled between the first UAV and a second UAV, wherein the second UAV receives power from the base station and communicates with the controller via the second cable.

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.

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 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 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).

An aerial drone system comprises: a first drone (14) comprising a first drone body and a first propeller system configured to propel the first drone through the air; a second drone (14) comprising a second drone body and a second propeller system configured to propel the second drone through the air; and an electronic media tether (36) coupled to the first drone and the second drone, wherein 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).

The present disclosure relates to an illumination unit for a helideck, comprising a mounting board, a light source attached to the mounting board, and a dome, and wherein a support structure comprises a separation wall air-tightly separating a first cavity under the dome from a second cavity receiving at least the mounting board and the light source. The separation wall further comprises a first wall portion forming an optical element, and wherein the optical element comprises one or more light entrance surfaces for receiving light from the light source and one or more light output surfaces for outputting light into the first cavity. The present disclosure also relates to light panels comprising a plurality of illumination units.

An aircraft light (2) comprises an arrangement of a plurality of light sources (12), arranged on a light source support (10), and a light guide (6) arranged for receiving and transmitting light emitted by the plurality of light sources (12). The light guide (6) comprises an optical fiber (5); a coupling portion (20) provided at an input end of the optical fiber (5) facing the plurality of light sources (12), the coupling portion (20) comprising a plurality of legs (22), with each of the plurality of legs (22) extending between the input end of the optical fiber (5) and a respective one of the plurality of light sources (12); and a light exit portion (8), providing light received and transmitted from the plurality of light sources (12) at a light head (9) of the aircraft light (2). The aircraft light (2) further comprises a light sensor (14), which is arranged among the plurality of light sources (12) for detecting stray light, emitted by the plurality of light sources (12) and not reaching the optical fiber (5).

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.

There is a remote control device or drone, which has software and a combination of lights or LED on an lighting ring or apparatus that can move independently of the drone; the drone can be programmed or be reactive to sound or other stimulus to create the effect of writing shapes or words in the air and typically at nighttime against a dark sky.

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.

Matrix lighting module with a plurality of light-emitting diodes (16-34) (LEDs) and with at least one primary optics (10) connected downstream of the LEDs (16-34), wherein at least one of the LEDs (16-34) is controllable independently of the other LEDs (16-34), and at least one aperture (38) is arranged between an LED (16-34) that is controllable independently of the other LEDs (16-34) and an adjacent LED (16-34), wherein the LEDs (16-34) are arranged on a plate (12), wherein the primary optics (10) extends at a distance from the plate (12), wherein the primary optics (10) and the plate (12) are connected via a housing (2), and wherein the at least one aperture (38) is arranged in the housing (2) between the primary optics (10) and the plate (12) is characterized in that a coupling surface (50) of the primary optics (10) with a convex projection section (52) extends towards a respective LED (16 - 34),wherein the at least one aperture (38) is arranged at a distance from the primary optics (10) in a region (56) between two convex projection sections (52) of the primary optics.,

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.

Embodiments are directed to systems and methods for providing light communication (LC) for an aircraft (101, 201). An LC transmitter (303) is mounted on an aircraft fuselage and is configured to broadcast light signals within a defined region outside the aircraft (101, 201). An LC receiver (313) mounted on the aircraft fuselage (101, 201) is configured to receive light signals broadcast by a remote LC device. A controller (307) is configured to manage LC signals in the aircraft (101, 201), and an interface (704) is provided between the controller (307) and an aircraft data network (309, 705). The light signals may be in a visible light spectrum, an invisible light spectrum, or both. The remote LC device may be, for example, a ground station (401, 401a, 402), an aircraft (502, 503), a ground vehicle, a ship, a building, or a portable transmitter.

An airfield ground lighting (AGL) system is configured to operate one or more constant current circuits of AGL lights according to a first mode of operation, referred to as conventional operation, and according to at least one second mode of operation, referred to as reduced current level operation. In the first mode of operation, a control unit implements a first dimming curve (20) for the AGL lights, in which a plurality of first constant current levels (A0, Ai, Amax) are associated with a plurality of first light intensity levels (X0, Xi, Xmax) output by the AGL lights. In the second mode of operation, the control unit implements a second dimming curve (30) for the AGL lights, in which a plurality of second constant current levels (B0, Bi, Bmax) are associated with a plurality of second light intensity levels output by the AGL lights. At least one, some or preferably all, of the plurality of second intensity levels is or are equal to at least one, some or preferably all of the plurality of first intensity levels (X0, Xi, Xmax). The second dimming curve implements at least one reduced current level compared to the first dimming curve for one or more same intensity level(s).

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.

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 exterior aircraft light (1) comprises a light source chamber (16), a comparative chamber (12), a support portion (4), wherein the support portion (4) is interposed between the light source chamber (16) and the comparative chamber (12), at least one light source (6), wherein the at least one light source (6) is arranged in the light source chamber (16), at least one optical element (8), arranged over the at least one light source (6) for shaping an exterior aircraft light output, a light transmissive cover (10), arranged over the at least one light source (6) and the at least one optical element (8) and closing the light source chamber (16), an airtight, elastic carrier (32), separating the light source chamber (16) from the comparative chamber (12), and a deformation sensor (47), which is arranged with the elastic carrier (32).

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 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.

An exterior aircraft light (1) comprises a mounting board (10), a light source (12) arranged on the mounting board (10), a lens (14) arranged over the light source (12), the lens (14) comprising a first lens portion (14a) on a first side of a cross-sectional center plane (20), which is orthogonal to the mounting board (10) and which runs through the light source (12), and comprising a second lens portion (14b) on a second side of the cross-sectional center plane (20), and a reflector (16), arranged to reflect light, emitted by the light source (12) into the first lens portion (14a), towards the second lens portion (14b), wherein the lens (14) fully encloses the light source (12) and the reflector (16).

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.