264results 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.

Apparatuses, systems, and methods are disclosed for establishing visually detectable ground markings, including in daylight, and designating visually detectable unsafe ground traffic areas from safe ground traffic areas proximate to and beneath an aircraft by providing visually detectable ground images formed from high intensity light energy sources located on an aircraft.

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 LED drone light of high power and very light weight has an LED circuit board cooled by a foamed metal matrix of copper or aluminum. Preferably bonded to a disc or puck which is thermally bonded to the back of the PCB, the foamed metal matrix can be cooled by a small fan attached to the light's housing.

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.

One embodiment is a rotorcraft comprising a fuselage; an empennage at an aft end of the fuselage; a tail rotor connected to the empennage; and a tail rotor guard (TRG) around the tail rotor, the TRG shrouding to the tail rotor; and a light emitting diode (LED) lighting element integrated into at least one surface of the TRG.

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 light (2) includes a support board (4); a light source (6), arranged on the support board (4); an optical element (8; 8'; 12; 14), arranged over the light source (6); and a kinematic coupling fixture (20), establishing a fixed position of the optical element (8; 8'; 12; 14) with respect to the support board (4).

A system and a method for contactless power generation for a lighting arrangement configured on an aircraft propeller. Power is produced when a magnetic field produced by an arrangement of magnets on an airframe magnetically interacts with coils configured on an aircraft propeller. When the propeller spins, rotation of the mounted coils through the magnetic fields of the magnets generate power. Electrical wiring carrying charge from the coils to the lights is laid into grooves formed in propeller blades which connect to lights inserted in formed sockets.

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.

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 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 active landing marker (100) including a housing (102), a cover panel (104), a marker panel (200) and an energy source (111, 112, 113) is provided. The cover panel (104) is coupled to the housing (102), and made of polarized translucent material. The marker panel (200) is positioned within the housing (102). The marker panel (200) includes a plurality of selectively positioned energy absorbing sections (240) and a plurality of energy transmission sections (220). The energy source (111, 112, 113) is contained within the housing (102). The marker panel (200) being positioned between the energy source (111, 112, 113) and the cover panel (104). Energy radiated from the energy source (111, 112, 113) passing through the energy transmission sections (220) of the marker panel (200) and through the cover panel (104) generating an active signal marker having a unique marker pattern. The active signal marker aiding in the landing of vehicles during varying environmental conditions.

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.

Techniques and examples related to single-channel line-of-sight (LOS) communications are described. A transmitting end of the LOS communication involves direct modulation of light emitted from an optical transmitter. A receiving end of the LOS communication involves receiving a video stream of the optical transmitter that emits the light, wherein the video stream includes a plurality of video frames that are temporally consecutive. The receiving end of the LOS communication also involves converting the video stream into a binary string including a plurality of binary bits. Each of the binary bits corresponds to a respective one of the plurality of video frames, and the binary string contains a repeating binary pattern representing a message being communicated. The receiving end of the LOS communication also involves extracting the binary pattern from the binary string and then decoding the binary pattern to obtain the message.

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

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.

Disclosed is an aircraft lighting system disposed in an environment of an aircraft. The system includes a housing. The system includes an illumination element disposed within the housing. The system includes energy generation circuitry configured to generate electricity from the environment. The system includes switching circuitry including a driver operable to control illumination of the illumination element and operated with a driver voltage. The system includes energy harvesting circuitry including a regulator configured to draw energy from the energy generation circuitry and output a regulator voltage at the driver voltage.

Methods, devices, and systems for airfield luminaire obstruction detection are described herein. In some examples, one or more embodiments include a controller for airfield luminaire obstruction detection, comprising a memory, and a processor configured to execute instructions stored in the memory to receive a signal from a light sensor of an airfield luminaire, determine, based on the signal, whether a lens of the airfield luminaire is obstructed by debris, and activate, based on whether the lens is obstructed, at least one of a vibration mechanism of the airfield luminaire and a heating mechanism of the airfield luminaire based on a temperature of the airfield luminaire to aid in clearing the debris.

The disclosure addresses an external lighting unit for an aircraft. This external lighting unit includes a lighting unit housing (310) have a mounting flange that is configured to provide a reduced contact with a supporting structure (e.g., a tail cone (60, 130) of an aircraft), which in turn reduces conductive heat transfer between the supporting structure and the lighting unit housing (310) (more specifically reduces conductive heat transfer between the supporting structure and a printed circuit board that is disposed within the lighting unit housing (310) and that may be seated on a portion of the lighting unit housing (310)). Open spaces on the surface of the mounting flange that face toward the supporting structure may be occupied by a thermal insulator (340).

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.

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.

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 buck 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.

An elongated aircraft cabin light (2) for illuminating a passenger cabin (104) of an aircraft (100) from a ceiling (110) of the passenger cabin (104) comprises: a row arrangement of a plurality of light modules (6, 8), extending along a longitudinal direction (L) of the elongated aircraft cabin light (2). Each of the plurality of light modules (6, 8) comprises at least one light source (10, 12, 14). The plurality of light modules (6, 8) include a plurality of intermediate light modules (6) and, on at least one end of the row arrangement, an end light module (8). Each of said plurality of intermediate light modules (6) is configured for emitting a downward light output (20) and at least one lateral light output (22) towards at least one lateral side. The end light module (8) is configured for emitting a supplementary downward light output (20); at least one supplementary lateral light output (22) towards at least one lateral side; and an upward light output (26), which is emitted from an end face (9) of the end light module (8). The upward light output (26) has a maximum light output intensity direction (MU), which is angled upwards with respect to the longitudinal direction (L) of the elongated aircraft cabin light (2).

A method may comprise: commanding, by a processor, a lighting system to generate a first desired effect in accordance with a first spectral weighting mode; determining, by the processor, a first optimized predetermined variable within a first predetermined domain to generate the desired effect based on the first spectral weighting mode; commanding, by the processor, the lighting system to transition from the first desired effect to a second desired effect, the second desired effect in accordance with a second spectral weighting mode; and determining by the processor, a second optimized predetermined variable within a second predetermined domain to generate the second desired effect based on the second spectral weighting mode, the first optimized predetermined variable being different from the second optimized predetermined variable.

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