A light assembly includes a housing, a light emitting diode (LED), and a hemispherical dome. The housing has a lens mounted thereon. The light LED is mounted within the housing and operable to emit light within a predetermined range of wavelengths and at an emission intensity toward the lens. The hemispherical dome mounted is within the housing between the LED and the lens. The hemispherical dome comprises a material that attenuates the emission intensity by a predetermined magnitude, and has an aperture formed therein and through which a portion of the light emitted from the LED may pass unattenuated.

An aircraft beacon light with integrated health monitoring comprises an annular arrangement of light sources, which are configured for repeatedly emitting beacon light flashes; a light detection sensor surrounded by the annular arrangement of light sources; and at least one reflective portion arranged to reflect light emitted by the annular arrangement of light sources onto the light detection sensor.

An aircraft exterior lighting multi-LED array for variable beam profile enables illumination of landing and taxi lights from a common fixture. An optic enables direction of luminance emitted from at least one central emitter (or cluster of emitters) along steradians illuminated when landing while directing luminance emitted from at least one peripheral emitter (or cluster of emitters) along steradians illuminated when taxiing.

A dynamic runway illumination system, including a light source having an addressable light beam direction, and a control unit configured to receive aircraft attitude information and the orientation of the runway selected for takeoff or landing, obtain horizontal and vertical axes, the horizontal axis being collinear with the takeoff or landing longitudinal direction, determine the actual and the reference aircraft trajectories, obtain the actual and the reference vertical approach angles, and the actual horizontal approach angle, and actuate onto the light source to perform an angular movement in the light beam direction of an absolute value of the actual vertical approach angle minus the absolute value of the reference vertical approach angle about the vertical axis, and an angular movement of an absolute value of the actual horizontal approach angle about the horizontal axis, to vertically and horizontally align the beam of the light source towards the runway direction.

Techniques and examples pertaining to single channel line-of-sight (LOS) communication are described. The transmitting end of the LOS communication involves direct modulation of a light emitted from a light emitter. The receiving end of the LOS communication involves receiving a video stream of the light emitter emitting the light, wherein the video stream comprises a plurality of video frames that are continuous in time. The receiving end of the LOS communication also involves converting the video stream to a binary string comprising 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 repeated binary pattern representing a message being conveyed. 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.

A light assembly may comprise a heatsink, a plurality of light emitting diodes, and a lens. The heatsink may include a first surface and a second surface opposite the first surface. The second surface may define an airflow path extending from a first end of the heatsink to a second end of the heatsink. The plurality of light emitting diodes may be coupled to the first surface of the heatsink. The lens may be located over the plurality of light emitting diodes and may contact the heatsink.

[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 body 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.

An unmanned aerial vehicle comprises a housing, a plurality of first arms, a plurality of second arms, and a landing gear. The housing includes a gimbal attachment to couple a gimbal with a camera. Each of the plurality of first arms and the plurality of second arms rotatably couple with the housing at one end and has a motor coupled with a propeller on the other end. The landing gear includes a plurality of foldable legs and releasably couples with an underside of the housing. The aerial vehicle may be programmed with aerial flight path data that corresponds with a prior traced route.

A self-powered, wireless lighting system for an aircraft evacuation system. The lighting system includes a piezoelectric sensor configured to generate electrical energy under an aircraft evacuation event when the aircraft evacuation system is deployed, and a first light source disposed on the aircraft evacuation system, the first light source configured to provide illumination to the aircraft evacuation system. The piezoelectric sensor is operably connected to the first light source and configured to supply electrical energy to the light source based on vibrations in the evacuation system during deployment of the evacuation system and during use of the evacuation system as passengers evacuate the aircraft.

A system for use in generating a power signal includes a first stage circuit having: a first input line coupled to a first stage first parallel line having a first stage first switch positioned thereon, a second input line coupled to a first stage second parallel line having a first stage second switch positioned thereon, and a first stage third parallel line oriented in parallel with the first stage first parallel line and the first stage second parallel line between a positive rail and a negative rail, the first stage third parallel line having a first capacitor positioned thereon. The system further includes a second stage circuit having a resonant inverter coupled between the positive rail and the negative rail and configured to output the power signal.