Abstract: An aircraft overhead passenger service unit comprises a plurality of oxygen masks for supplying oxygen to aircraft passengers in an emergency situation; and at least two different oxygen mask storage portions, which are spaced apart from each other in a longitudinal direction (L). The plurality of oxygen masks are stored in the at least two different oxygen mask storage portions. The aircraft overhead passenger service unit further comprises an oxygen mask controller, which is switchable between at least two different configurations. The at least two different oxygen mask storage portions are individually associated with the at least two different configurations, with each of the at least two different configurations effecting a release of only the oxygen masks of the associated oxygen mask storage portion in the emergency situation.

Abstract: An aircraft passenger reading light, which is operable in at least two predetermined configurations, comprises: a light source; an optical element; and an actuation mechanism, which is configured to modify a distance between the light source and the optical element. The distance (D) between the light source and the optical element differs in the at least two predetermined configurations and a spatial extension of the illumination, which results from the light output of the light source and the optical element, differs in the at least two predetermined configurations.

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: 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: 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.

Abstract: 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.

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: A system for providing and monitoring UV illumination in an interior of an aircraft includes at least one switchable UV light source; a light detector, responsive to visible light and UV light and configured for providing sensor outputs regarding detected light; and a controller for monitoring an operational status of the at least one switchable UV light source. The controller is configured to determine the operational status of the at least one switchable UV light source by comparing a first sensor output, provided by the light detector when the at least one switchable UV light source is activated, with a second sensor output, provided by the light detector when the at least one switchable UV light source is deactivated.

Abstract: An exterior aircraft light includes a mounting board, a light source arranged on the mounting board and a lens arranged over the light source. The lens includes a first lens portion on a first side of a cross-sectional center plane, which is orthogonal to the mounting board and which runs through the light source, and a second lens portion on a second side of the cross-sectional center plane. The light also includes a reflector, arranged to reflect light, emitted by the light source into the first lens portion, towards the second lens portion, wherein the lens fully encloses the light source and the reflector.

Abstract: A navigation light system for an unmanned aerial vehicle, such as a multicopter type unmanned aerial vehicle, includes: a plurality of light emission units. E of the plurality of light emission units has a unit-specific light emission direction and is configured to provide a light output around the unit-specific light emission direction. Each of the plurality of light emission units includes a multi-color light source capable of emitting red light, green light, and white light. The plurality of light emission units are arranged to jointly provide a navigation light pattern around the unmanned aerial vehicle and wherein the light outputs of adjacent light emission units have an overlap the navigation light system is configured to operate each of the plurality of light emission units depending on a relation between a momentary flight direction of the unmanned aerial vehicle and the respective unit-specific light emission direction.

Abstract: An exterior aircraft light cover with integrated illumination includes a mounting portion, configured to be mounted to an exterior aircraft light housing; a light transmissive pane, supported by the mounting portion. The mounting portion and the light transmissive pane are configured to jointly close the exterior aircraft light housing. The cover also includes at least one photovoltaic device, which is configured for generating electric energy when illuminated; at least one electric storage device, which is configured for storing the electric energy generated by the at least one photovoltaic device; and at least one ancillary light source, which is operable with electric energy supplied by at least one of the at least one photovoltaic device and the at least one electric storage device.

Abstract: Rotorcraft lighting equipment includes a plurality of lighting devices configured to be mounted to an exterior of a rotorcraft, wherein each of the lighting devices comprises a plurality of individually controllable lighting modules which are configured for emitting light into different spatial directions; and a lighting control device configured for individually controlling the operation of the plurality of lighting modules for generating a desired light distribution of the light emitted by the plurality of lighting modules.

Abstract: An illuminated aircraft passenger cabin gasper comprises an air outlet for outputting a flow of air into an aircraft passenger cabin and an air guide, movably arranged within the air outlet for adjusting the flow of air that includes a light guide. The gasper also includes at least one light source, arranged adjacent to the light guide for coupling light into the light guide. The light guide has a light output surface for coupling light out of the light guide into the aircraft passenger cabin.

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 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: 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.

Abstract: An exterior aircraft light includes 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 the housing having a front end region and a rear end region, wherein the housing is configured to be mounted on a tail portion of a fuselage of an aircraft; at least one first light source, arranged in the rear end region of the housing, for providing aircraft rearward signal lighting; and a plurality of second light sources, which are arranged spaced along the length (L) of the housing for a distributed illumination of a stabilizer of the aircraft.

Abstract: An aircraft beacon light unit has an operating light emission distribution. The operating light emission distribution has a first light emission opening angle of at least 150° in a first cross-sectional plane, and a second light emission opening angle of at most 180° in a second cross-sectional plane orthogonal to the first cross-sectional plane. The aircraft beacon light unit is configured in such a way that it is mountable to an aircraft with the first cross-sectional plane being oriented in a vertical direction and the second cross-sectional plane being oriented in a horizontal direction, and the first light emission opening angle extends at least 75° both above and below the second cross-sectional plane.

Abstract: An electric aircraft emergency power supply module includes at least one electric power cell for storing and supplying electric energy and a controller for controlling charging and discharging of the at least one electric power cell and for determining a charging level of the at least one electric power cell. The controller includes a simulator, which is configured for simulating an electric behavior of at least one temperature sensitive element as a function of the charging level of the at least one electric power cell.

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.