A pane assembly (2) for a window (8) arranged in the outer wall (4) of an aircraft (6) in a window plane (10) contains a transparent cover pane (12) in a cover plane (14), a switching film (16) in a scattering plane (18), which is switchable between a transparent state (ZT) and a diffuse state (ZD), a luminous film (20) in a light plane (22) having LEDs (24), wherein a spacing (A) between each two LEDs (24) in relation to one another is at least five times their transverse extension (Q), wherein the pane assembly (2) is arranged in front of the window (8) in an installed state (M), so that scattering plane (18), light plane (22), and window plane (10) extend in parallel to one another and the luminous film (20) is arranged between the window (8) and the switching film (16), and window (8), switching film (16), and luminous film (20) are located aligned one behind another on the line of sight (26).

A window assembly (40) contains the window (8) and the pane assembly (2) arranged in front of it in the installed state (M).

An aircraft beacon light includes a light source carrier, wherein the light source carrier comprises a plurality of connection fields, with the plurality of connection fields forming at least two polygonal connection structures on the light source carrier. The beacon also includes a plurality of LED modules, with the plurality of LED modules being arranged along a particular one of the at least two polygonal connection structures and with each of the plurality of LED modules being coupled to a respective connection field of said particular one of the at least two polygonal connection structures.

An integrated multimode thermal energy transfer system, method and apparatus for full-scale clean fuel electric-powered multirotor aircraft with automatic on-board-capability to provide sensor-based temperature awareness and adjustment to critical components and zones of the aircraft. Automatic computer monitoring, including by a programmed triple-redundant digital autopilot computer, controls each motor-controller and motor to produce pitch, bank, yaw and elevation, while simultaneously measuring, calculating, and adjusting temperature and heat transfer of aircraft components and zones, to protect critical components from exceeding operating parameters and to provide a safe, comfortable environment for occupants during flight. By using the results of the measurements to inform computer monitoring, the methods and systems can use byproducts including thermal energy disparities and differentials related to both fuel supply systems and power generating systems to both add and remove heat from different aircraft zones to improve aircraft function, comfort, and efficiency.

A lighting apparatus includes a plurality of LEDs arranged in a row on an elongated wiring board; and a lens covering all the LEDs and controlling distribution of light emitted from each LED. An optical axis of the light emitted from each LED is orthogonal to the wiring board. The lens has a light emitting surface that controls distribution of the light emitted from each LED. When the light emitting surface is divided into at least three regions, the lens performs light distribution such that light radiated from a region is distributed in a direction tilted with respect to the optical axis of the light emitted from the LED. Thus, asymmetric distribution of light is achieved when the optical axis of the light from the LED is the axis of symmetry, and further, the luminous flux in the direction tilted with respect to the optical axis is increased most.

An exterior aircraft navigation light for an aircraft having a nominal forward flight direction and being able to fly into the nominal forward flight direction as well as into a plurality of further flight directions, such as sideways or backwards, has at least one light emission unit and control circuitry coupled to the at least one light emission unit, wherein the exterior aircraft navigation light is configured such that each of the at least one light emission unit has a unit-specific light emission direction that has a predefined horizontal angle with respect to the nominal forward flight direction, and wherein each of the at least one light emission unit includes a multi-color light source configured to emit red light, white light and green light, and an optical system for conditioning the red light, the white light and the green light emitted by the multi-color light source.

A propeller health monitoring system for an aircraft includes an aircraft having one or more propellers that includes light in or on them. The system includes one or more receptors mounted to a fuselage or a nacelle of the aircraft, each receptor having a sensor surface which is able to detect a position for each light beam crossing over the sensor surface as the propeller rotates, such that the receptor generates a signal that is indicative of the position as a measure of blade tip trajectory for each passing propeller blade The system also includes a processing unit which analyses the signals from the receptor to determine health of the propeller blades of the one or more propellers based on where the beams of light from the propeller blades have crossed over the sensor surface.

A lighting device for an airport runway with a base carrier, at which at least one lighting unit is fastened, with the lighting unit comprising a light source, a reflector, and a covering glass panel, with the light source and the reflector being combined to a joint lighting module, with the light source and the reflector being assembled on a joint carrier of the lighting module connected to the base carrier in a detachable fashion.

In a lighting arrangement (2) for an interior (4) of a vehicle, having a beam area (6) for emitting light (8) into an environment (10) of the lighting arrangement (2), having at least one first luminaire (12a, b) having a first luminous area (14a, b) for emitting the light (8), the first luminous area (14a, b) being part of the beam area (6), having at least one projector (16) with a beam opening (18) for emitting the light (8), the beam opening (18) being part of the beam area (6), at least one of the first luminaires (12a, b) has at least one passage region (34) for at least one part of one of the beam openings (18) of one of the projectors (16) on its first luminous area (14a, b), and/or, in at least one of the projectors (16), a surface region (20) of the projector (16) which is adjacent to the beam opening (18) is in the form of a second luminaire (21) having a second luminous area (22) for emitting light (8), the second luminous area (22) being part of the beam area (6).

An interior aircraft light includes a mounting structure for mounting the interior aircraft light to an aircraft seat; a UV radiation source; and an optical system, configured to direct UV radiation from the UV radiation source towards a floor portion underneath the aircraft seat.

A runway-embedded flash lighting device, includes a body configured to be embedded in a runway; a ceiling member including a flash emission window and disposed in an upper opening of the body and configured to be exposed to a runway surface when the body is embedded in the runway; a light guide member disposed in the flash emission window; an LED flash light source disposed inside the body and configured to emit a flash toward the light guide member; and a heat conducting member, wherein the light guide is configured to allow the flash emitted from the LED flash light source to be emitted from the flash emission window, the heat conducting member is disposed inside the body and includes a first part in contact with the LED flash light source, and a second part in contact with the ceiling member.