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: Aircraft headlight includes at least one light source; and a light transmissive cover, at least partially covering the at least one light source. The light transmissive cover includes a first layer made of a first material; a second layer made of a second material, which differs from the first material; and at least one electric heating wire for heating the light transmissive cover by passing an electric current through the electric heating wire. The at least one electric heating wire is embedded into the first layer.

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 navigation light, configured to be usable as any of a left forward navigation light, a right forward navigation light, and a tail navigation light of an aircraft, comprises a common support plate which is substantially vertical in the aircraft frame of reference; a first light source arranged on the common support plate for emitting red light; a second light source arranged on the common support plate for emitting green light; a third light source arranged on the common support plate for emitting white light; a driving circuit coupled to the first light source, the second light source and the third light source and configured to supply power to a selected one of the first light source, the second light source, and the third light source; and a blocking element arranged to limit the light output of the aircraft navigation light to one lateral side.

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 exterior aircraft light that can be used on an aircraft includes a dome-shaped light transmissive cover, a light emission assembly, and an interface assembly. The light emission assembly comprises a light emission tower portion, having a cover-facing end and an opposite aircraft-facing end and having a hollow channel extending between the aircraft-facing end and the cover-facing end, a platform portion, and at least one light source and at least one optical element, arranged on the platform portion. The interface assembly extends through the hollow channel of the light emission tower portion and comprises an elevated base, which is configured for mechanically supporting and electrically connecting an electric component, the electric component being at least one of a data reception component, a data transmission component, and a data generation component. The interface assembly further comprises at least one signal line, which extends from the elevated base through the interface assembly.

Abstract: An aircraft anti-collision light includes a first group of light sources arranged in a first annular configuration around an axis (A) and a second group of light sources arranged in a second annular configuration. The first group of light sources is surrounded by the second group of light sources. The light also has a first lens structure, which is configured for generating a first light output from light emitted by the first group of light sources, a second lens structure, which is configured for generating a second light output from light emitted by the second group of light sources, and a light transmissive cover, which is arranged over the first lens structure and the second lens structure and which passes the first light output and the second light output for emitting a total light output.

Abstract: 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.

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: 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: A method of indicating a flight direction of an aerial vehicle, having a vehicle body and a plurality of rotors supported by the vehicle body, includes: on the basis of a momentary flight direction of the aerial vehicle, controlling a matrix of light sources, in particular a matrix of LEDs, which are mounted to the vehicle body of the aerial vehicle, to provide an illumination pattern to an observer of the aerial vehicle, with the illumination pattern comprising a flight direction indication, indicative of the momentary flight direction of the aerial vehicle.

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 navigation light, configured to be usable as any of a left forward navigation light, a right forward navigation light, and a tail navigation light of an aircraft, comprises a common support plate which is substantially vertical in the aircraft frame of reference; a first light source arranged on the common support plate for emitting red light; a second light source arranged on the common support plate for emitting green light; a third light source arranged on the common support plate for emitting white light; a driving circuit coupled to the first light source, the second light source and the third light source and configured to supply power to a selected one of the first light source, the second light source, and the third light source; and a blocking element arranged to limit the light output of the aircraft navigation light to one lateral side.

Abstract: An aircraft light (2) includes a support board (4); a light source (6), arranged on the support board (4); an optical element (8; 8?; 12; 14), arranged over the light source (6); and a kinematic coupling fixture (20), establishing a fixed position of the optical element (8; 8?; 12; 14) with respect to the support board (4).

Abstract: A helicopter search light includes a movable light head comprising: at least one light source and at least one optical element, which are configured for emitting a search light beam; at least two radiation sensors arranged in a preset distance (d) from each other. The radiation sensors are configured for detecting electromagnetic radiation and providing corresponding sensor signals. The system also includes an image processing module configured for receiving the sensor signals provided by the at least two radiation sensors and generating enhanced image data from said sensor signals and a controller configured for controlling movement of the movable light head depending on said enhanced image data.

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 aircraft passenger reading light comprises at least one reading light source, which is arranged for emitting visible light in a reading light emission direction; and at least one infrared light source, which is arranged for emitting infrared light in an infrared light emission direction. The infrared light emission direction is inclined with respect to the reading light emission direction.

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.