Abstract: A combined aircraft navigation and anti-collision light, includes: at least one navigation light source and one anti-collision light source; a navigation light sensor, in operation outputting a light detection signal corresponding to an amount of light detected by the navigation light sensor; first and second optical systems, associated with navigation and collision light sources, wherein the first optical system is configured for shaping a navigation light output from light emitted by the at least one navigation light source and is configured for directing stray light from the at least one navigation light source to the navigation light sensor and a second optical system, associated with the at least one anti-collision light source and configured for shaping an anti-collision light output from light emitted by the at least one anti-collision light source; a lens cover, arranged over the light sources and optical systems for passing light therethrough.

Abstract: A lighting arrangement includes a light source configured for emitting light; a first reflector configured for collimating a first portion of the light emitted by the light source around a main light emission direction (D); and a second reflector arranged opposite to the light source. The second reflector is configured for reflecting a second portion of the light emitted by the light source back towards the light source for being diffusely reflected from the light source.

Abstract: An exterior lamp for an aircraft may comprise a housing, a navigation light disposed within the housing, and a brake light disposed within the housing, wherein the brake light is configured to illuminate in response to a brake signal. The exterior lamp may include a controller disposed within the housing, and a tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising receiving a brake signal and illuminating the brake light in response to a brake signal.

Abstract: An aircraft light for a foldable wing tip of an aircraft includes a first lighting structure, including at least one first light source and a first optical system, with the at least one first light source and the first optical system in operation generating a first light output; a second lighting structure, including at least one second light source and a second optical system, with the at least one second light source and the second optical system in operation generating a second light output; wherein the first light output and the second light output are of the same color and wherein the first light output and the second light output are angled with respect to each other; and wherein the aircraft light is configured to control the at least one first light source and the at least one second light source depending on a wing tip orientation signal, which is indicative of an orientation of the foldable wing tip.

Abstract: An aircraft beacon light includes a mounting plate having a central portion; a plurality of light sources arranged on the mounting plate around the central portion and facing away from the mounting plate; and a lens structure arranged over the plurality of light sources, wherein the lens structure is configured to reflect a first portion of light emitted by the plurality of light sources laterally outwards via total internal reflection; wherein the aircraft beacon light is configured to emit flashes of red light in operation.

Abstract: An aircraft light comprises at least one light source; at least one sensor, an operating mode selector, and a transmitter. The sensor is configured for detecting current operational conditions and providing at least one corresponding sensor signal. The operating mode selector configured for determining a suitable light emission of the at least one light source based on the at least one sensor signal. The operating mode selector is further configured for determining the amount of electrical power needed for generating the determined light emission. The transmitter configured for transmitting a power request signal indicating the determined amount of electrical power to a power supply.

Abstract: An exterior lamp for an aircraft may comprise a housing, a navigation light disposed within the housing, and a brake light disposed within the housing, wherein the brake light is configured to illuminate in response to a brake signal. The exterior lamp may include a controller disposed within the housing, and a tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising receiving a brake signal and illuminating the brake light in response to a brake signal.

Abstract: A helicopter anti-bird-collision system including a search light (2) and a control unit (35) which is configured for operating the search light (2) in a flash light mode by switching the search light periodically on and off.

Abstract: An aircraft lighting device includes a circuit board; an LED soldered to the circuit board; an optical element supported by the circuit board and positioned for re-directing at least part of the light emitted by the LED; a magnetic coupling between the circuit board and the optical element; and at least one surface mounted device included in the optical element, such surface mounted device including a pin soldered to the circuit board.

Abstract: An aircraft navigation light includes: a navigation lighting arrangement, having: a power input, couple able to an aircraft on-board power supply network, at least one navigation light source, and a power conditioning circuit, coupled between the power input and the at least one navigation light source for conditioning a power flow from the power input to the at least one navigation light source; an auxiliary power supply, coupled to the power conditioning circuit for diverting power from the navigation lighting arrangement; and a power supply output, coupled to the auxiliary power supply, for supplying power from the auxiliary power supply to an exterior aircraft light, external to the aircraft navigation light.

Abstract: A system for transferring heat from printed circuit boards (PCBs) with light emitting diodes (LEDs) includes a PCB having a first side and a second side and configured to be coupled to an exterior portion of an aircraft. The system further includes a LED located on the first side of the PCB. The system further includes a first metal strip located on the second side of the PCB. The system further includes a heat sink configured to contact the first metal strip to dissipate heat from the PCB.

Abstract: An aircraft beacon light for being mounted to an aircraft fuselage includes: a support structure, having a carrier, and a stem for supporting the carrier and for spacing the carrier from the aircraft fuselage; and a lighting system, supported by the support structure, the lighting system having a plurality of light sources, light optics for redirecting at least a portion of the light emitted by the plurality of light sources, and a lens cover, with the plurality of light sources and the light optics being arranged between the carrier and the lens cover; wherein the aircraft beacon light is configured to emit a red-flashing beacon light output in operation.

Abstract: A drain valve for draining liquid from an enclosed space comprises a movable plunger, which is movable between a closed position in which the plunger does not allow liquid to flow through the drain valve, and at least one open position, in which the plunger allows liquid to flow through the drain valve; and an elastic element, which is configured to urge the movable plunger into its closed position. The plunger is provided with at least one duct extending through the plunger and allowing fluid to flow through the drain valve when the plunger is positioned in its closed position, wherein said at least one duct is closed by a semi-permeable medium, which is permeable for air and water vapor and impermeable for liquid water.

Abstract: A cover for an exterior aircraft light includes a lens cover structure, attachable to an exterior aircraft light housing and configured to close the exterior aircraft light housing, wherein the lens cover structure has an inside and an outside and is at least partially made of transparent material; and a wear indicator, attached to the inside of the lens cover structure, the wear indicator having a contrasted pattern visible from the outside of the lens cover structure through the transparent material.

Abstract: A method of emitting an anti-collision light output from an unmanned aerial vehicle includes emitting a plurality of light flashes of different colors within a flash duration interval, with the flash duration interval being at most 0.2 s; wherein the plurality of light flashes within the flash duration interval comprise at least one blue light flash and at least one yellow light flash or wherein the plurality of light flashes within the flash duration interval comprise at least one cyan light flash, at least one magenta light flash, and at least one yellow light flash.

Abstract: An exterior aircraft light for indicating a movement of a foldable wing tip between a folded up position and a laterally extended position includes a light source; and a control unit; wherein the control unit is configured to operate the light source to emit a warning light output in response to a warning light control signal indicative of the movement of the foldable wing tip.

Abstract: An aircraft beacon light for being mounted to an aircraft fuselage includes: a support structure, having a carrier, and a stem for supporting the carrier and for spacing the carrier from the aircraft fuselage; and a lighting system, supported by the support structure, the lighting system having a plurality of light sources, light optics for redirecting at least a portion of the light emitted by the plurality of light sources, and a lens cover, with the plurality of light sources and the light optics being arranged between the carrier and the lens cover; wherein the aircraft beacon light is configured to emit a red-flashing beacon light output in operation.

Abstract: A ground illumination aircraft light unit includes a mounting portion, which is configured for mounting the light unit to an aircraft; a transparent cover, which is mounted to the mounting portion and in combination with the mounting portion defines an interior space of the light unit; and at least one light source, which is arranged within the interior space of the light unit and which is configured for emitting light for illuminating an airfield in the vicinity of the aircraft. The light unit is configured to emit predominantly p-polarized light in a predefined spatial sector; and to emit non-polarized light in an area outside said predefined spatial sector.

Abstract: An exterior aircraft light unit includes at least two light sources. Each light source is provided with a variable current bypass component. Each variable current bypass component is configured to allow bypassing an adjustable electric current by the respective light source.

Abstract: An aircraft vertical stabilizer illumination light, configured to illuminate a vertical stabilizer of an aircraft, has a housing having a length (L), a width (W), and a height (H), the length (L) being greater than the width (W) and the height (H); and a plurality of light sources being arranged spaced along the length (L) of the housing (8) for a distributed illumination of the vertical stabilizer, wherein the housing (8) is configured to be mounted adjacent the vertical stabilizer on a tail portion of a fuselage of the aircraft.