Abstract: An exterior aircraft light with cover erosion monitoring, the exterior aircraft light comprises: a support; at least one light source, arranged on the support; a light transmissive cover, arranged over the at least one light source, the light transmissive cover having a forward facing portion and a rear-ward facing portion; a first light sensor, arranged to receive light emitted by the at least one light source and reflected towards the first light sensor by the forward facing portion of the light transmissive cover; and a second light sensor, arranged to receive light emitted by the at least one light source and reflected towards the second light sensor by the rearward facing portion of the light transmissive cover.

Abstract: An aircraft beacon light includes: a plurality of first LEDs, wherein the plurality of first LEDs emit aviation red light in accordance with Federal Aviation Regulations section 25.1397 at an operating temperature of 25° C.; and a plurality of second LEDs, wherein the plurality of second LEDs are phosphor-converted LEDs of red or reddish orange color; wherein the aircraft beacon light is configured to jointly flash the plurality of first LEDs and the plurality of second LEDs for emitting a red beacon light output.

Abstract: An aircraft light providing a white light output has a light source that comprises a light emitting semiconductor for emitting light having an initial light spectrum; a first light converting material, arranged over the light emitting semiconductor; and a light transmissive layer, covering the first light converting material. A first portion of the light, which is emitted by the light emitting semiconductor, is shifted towards longer wavelengths by the first light converting material. The aircraft light further comprises a second light converting material, which is arranged over the light transmissive layer of the light source and a lens element, which is arranged over the second light converting material, with light exiting the lens element forming at least a portion of the white light output of the aircraft light.

Abstract: An aircraft beacon light comprises an annular light source support having a plurality of light passing portions; a plurality of light sources, arranged on the annular light source support for a radially outwards emission of light flashes; a light detector for sensing a light output level of at least a subset of the plurality of light sources; and at least one optical element for shaping a beacon light output from light emitted by the plurality of light sources, the at least one optical element having at least one light guiding portion for capturing stray light from at least said subset of the plurality of light sources and for guiding said stray light through the plurality of light passing portions and towards the light detector.

Abstract: 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.

Abstract: A multi mode aircraft beacon light comprises a mounting portion for mounting the multi mode aircraft beacon light to an aircraft fuselage; at least one visible light source for emitting a visible beacon light output; a plurality of infra-red light sources for emitting an infrared beacon light output; an orientation sensor; and a controller, coupled to the orientation sensor for receiving an orientation sensor signal from the orientation sensor. The controller is configured to determine a mounting orientation of the multi mode aircraft beacon light from the orientation sensor signal, wherein the mounting orientation is indicative of whether the multi mode aircraft beacon light has an upper fuselage mounting position or a lower fuselage mounting position; and to selectively operate the plurality of infrared light sources, depending on the mounting orientation of the multi mode aircraft beacon light.

Abstract: An exterior aircraft light with cover erosion monitoring, the exterior aircraft light comprises: a support; at least one light source, arranged on the support; a light transmissive cover, arranged over the at least one light source, the light transmissive cover having a forward facing portion and a rear-ward facing portion; a first light sensor, arranged to receive light emitted by the at least one light source and reflected towards the first light sensor by the forward facing portion of the light transmissive cover; and a second light sensor, arranged to receive light emitted by the at least one light source and reflected towards the second light sensor by the rearward facing portion of the light transmissive cover.

Abstract: An exterior aircraft light with integrated light output monitoring includes a light source support, at least one light source, arranged on an outward facing side of the light source support, an aperture in the light source support, a light collection surface, arranged to direct an output monitoring light portion of the light, emitted by the at least one light source, through the aperture in a predefined angular range with respect to the light source support. The light also includes a light detector, arranged on a back side of the light source support, and a total internal reflection optical element, arranged to direct the output monitoring light portion, having travelled through the aperture in the predefined angular range with respect to the light source support, to the light detector via total internal reflection.

Abstract: An aircraft headlight includes at least one visible light source for emitting a headlight light output; a light transmissive cover, at least partially covering the at least one visible light source; and at least one infrared emitter for emitting infrared radiation. At least 90% of radiation energy, comprised in the infrared radiation emitted by the at least infrared emitter, is emitted within a predefined wavelength range; and the light transmissive cover allows at least 25%, in particular at least 30%, more particularly at least 45%, of the radiation energy, which is emitted within the predefined wavelength range, to pass through the light transmissive cover.

Abstract: An autonomous search light system for being mounted to an aircraft includes a search light for emitting an adjustable light output; an RF receiver with at least two RF antennas for receiving RF signals emitted by an RF transmitter; and a controller for determining a position of the RF transmitter in relation to the search light from the received RF signals and for controlling the search light based on the determined position of the RF transmitter.

Abstract: An aircraft passenger cabin light. The light has: an elongated shape having a longitudinal direction (L) comprises: a cabin wall illumination assembly, which extends along the longitudinal direction (L) of the aircraft passenger cabin light and which is configured for illuminating a portion of a wall of an aircraft passenger cabin; and a plurality of personal reading light units for providing personal reading light illumination to passengers. The plurality of personal reading light units are arranged in an array extending along the longitudinal direction (L) of the aircraft passenger cabin light Said array is arranged along the cabin wall illumination assembly.

Abstract: An exterior aircraft light with integrated light output monitoring includes a light source support, at least one light source, arranged on an outward facing side of the light source support, an aperture in the light source support, a light collection surface, arranged to direct an output monitoring light portion of the light, emitted by the at least one light source, through the aperture in a predefined angular range with respect to the light source support. The light also includes a light detector, arranged on a back side of the light source support, and a total internal reflection optical element, arranged to direct the output monitoring light portion, having travelled through the aperture in the predefined angular range with respect to the light source support, to the light detector via total internal reflection.

Abstract: A canopy is configured to be mounted to a passenger seat of a passenger transport vehicle, in particular an aircraft. The canopy is foldable between a retracted storage configuration and an extended operational configuration. In the operational configuration, the canopy forms a hood establishing a passenger's personal space below the canopy. The canopy comprises at least one functional device which is configured for modifying a physical characteristics of the personal space. The at least one functional device in particular includes at least one of a lighting device configured for lighting the personal space and a venting device configured for venting the personal space.

Abstract: An aircraft light includes a support board and a supporting profile. The support board supports at least one electric light source, in particular at least one LED. The support board has two lateral edges, which extend in a longitudinal direction of the support board and which are spaced apart from each other in a transverse direction (T) of the support board. The supporting profile comprises a receiving space for receiving and supporting the support board. The receiving space is defined by a base, extending in a longitudinal direction (L) of the supporting profile and in a transverse direction (T) of the supporting profile, and two opposing side walls protruding from the base. The supporting profile further comprises two undercut sections, forming opposing slots in the two opposing side walls that are dimensioned for accommodating a lateral edge of the support board, respectively.

Abstract: A protective cover for a fuselage-mounted exterior aircraft light includes a fuselage-facing mounting side for mounting the protective cover to an exterior aircraft light housing or to an exterior skin of an aircraft; a light transmissive forward facing light emission surface; and an air deflection zone, which is shaped to direct a portion of an impinging air stream (A) along and over the forward facing light emission surface for shielding the forward facing light emission surface from the impinging air stream (A).

Abstract: An aircraft light comprises a support board; a light source, arranged on the support board; a first optical element, which is at least partially light transmissive, which is arranged over the light source, and which is fixed to the support board; and a second optical element, which is at least partially light transmissive, wherein the first optical element is interposed between the light source and the second optical element. The first optical element has a first engagement portion and the second optical element has a second engagement portion. The first engagement portion and the second engagement portion establish a positive fit between the first optical element and the second optical element. At least a portion of light, which is emitted by the light source in operation, passes through the first optical element and through the second optical element.

Abstract: A method of determining operating conditions of an exterior aircraft light comprising at least one light source includes: operating the at least one light source of the exterior aircraft light; repeatedly detecting light with a light detector, which is located at the exterior aircraft light and configured for providing light detection values; determining a smallest light detection value (Imin) provided by the light detector within a first period of time, and storing said smallest light detection value (Imin) as an element of a series of smallest light detection values (Imin); and evaluating the light detection values and the series of smallest light detection values (Imin) for detecting erosion of an optical component of the exterior aircraft light, for detecting the presence of ambient light and/or for detecting the presence of fog and/or clouds in front of the exterior aircraft light.

Abstract: An aircraft beacon light comprises an annular light source support having a plurality of light passing portions; a plurality of light sources, arranged on the annular light source support for a radially outwards emission of light flashes; a light detector for sensing a light output level of at least a subset of the plurality of light sources; and at least one optical element for shaping a beacon light output from light emitted by the plurality of light sources, the at least one optical element having at least one light guiding portion for capturing stray light from at least said subset of the plurality of light sources and for guiding said stray light through the plurality of light passing portions and towards the light detector.

Abstract: The invention relates to a method for capturing an absolute rotational position of a shaft using at least two rotational material measures which are synchronously coupled to the shaft, comprising material measures with a different number of graduations which are each relatively prime in pairs, a determination of the state of the individual material measures by means of sensors, wherein a quantizable number of rotational states Ni is captured for each material measure, the total measurement range of the capture system is determined by the product N=?i=1 Ni of the possible states of all material measure, and each combination of states (a0, a1, a2, . . . , an) occurs exactly once within the total measurement range N, with the result that the absolute position of the shaft can be determined at any time from the combination of states of the material measures.

Abstract: A cargo handling system is disclosed herein. The cargo handling system includes a conveyance surface a power drive unit for moving cargo along the conveyance surface where the power drive unit disposed in the conveyance surface and a cargo detector coupled to the power drive unit. The cargo detector includes an image sensor having a sensing surface, the sensing surface being oriented towards the cargo, a shutter disposed between the image sensor and the cargo, and a pin hole disposed in the shutter.