An aircraft exterior light unit may comprise a magnetically controlled fluid drain valve configured to expel liquid water from the light unit. The valve may include a permanent magnet configured to induce a magnetic flux circuit that generates a magnetic force configured to close the valve. The valve may be configured to open when the pressure inside the light unit exceeds the magnetic force. As the valve opens and expels the water, the pressure within the light unit may decrease, equalizing with that of the external environment. As the magnetic force generated by the magnet increases as the valve is open and the water expelled, the magnet may be configured to close the valve once more. As such, the magnet may be configured to control a self-acting fluid drain valve in an aircraft exterior light.

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).

A lighting fixture includes a light source holder, a pair of position adjustors, and an outer shell. The light source holder holds a light source. The position adjustors are arranged to face each other and interpose the light source holder between themselves and supports the light source holder to allow the light source holder to rotate around a first virtual axis defined as a virtual axis passing through the position adjustors. The outer shell has an opening in which the light source holder and the position adjustors are arranged and supports the position adjustors to allow the position adjustors to rotate around a second virtual axis defined by a normal to an opening plane of the opening. The first virtual axis intersects with the second virtual axis and is located either within or behind the opening plane.

The present invention is a lighting fixture device with a frustoconical housing. The frustoconical housing has a housing edge and an inner housing chamber accessible by a housing aperture. This inner housing chamber includes a parabolic reflective surface with multiple symmetrical reflective sections. Each reflective section includes at least one focal point. The device also includes an LED board mounting post forming a vertical axis through the vertex of the parabolic reflective surface. The LED board mounting post includes at least one mounting surface, to which is mounted multiple LED boards. Each LED board includes at least one LED. A central axis of each LED is aligned with at least one of the focal points.

An aircraft beacon light for an aircraft wing with a foldable wing tip includes a housing, a lens cover, and at least one light source arranged between the housing and the lens cover, wherein the aircraft beacon light is configured to emit flashes of red light in operation, and wherein the housing and the lens cover are shaped to embed the aircraft beacon light into a hinge assembly coupling the foldable wing tip to a main wing portion of the aircraft wing.

An exterior aircraft light unit includes a mounting structure, a plurality of first light sources arranged on the mounting structure, and a lens cover arranged over the plurality of first light sources, the lens cover having a convex shape at least in a first cross-sectional plane, wherein the plurality of first light sources are arranged in a curved pattern, with the curved pattern having the same direction of curvature as the convex shape of the lens cover in the first cross-sectional plane.

An exterior aircraft light includes a base plate and a plurality of lighting units arranged on the base plate, wherein each of the plurality of lighting units includes an elongated LED light source for emitting light, the elongated LED light source having a light emitting surface with a longitudinal extension and a transverse extension, with the longitudinal extension being greater than the transverse extension and with a projection of the longitudinal extension onto the base plate defining an orientation direction of the elongated LED light source, and a collimating optical system for collimating the light emitted by the elongated LED light source towards a main output direction, wherein the plurality of lighting units has at least a first lighting unit and a second lighting unit.

An aircraft light unit (2), has a support portion (4), a light source having at least one LED (6), the light source being arranged on the support portion (4) and in operation emitting light with a source-side light intensity distribution, and an optical element (8) for transforming the source-side light intensity distribution into an output light intensity distribution. The optical element (8) has at least two transformation segments (10, 20, 30), covering different angular ranges of the source-side light intensity distribution in a first cross-sectional plane. The at least two transformation segments (10, 20, 30) include a first transformation segment (10), with the light from the light source experiencing total internal reflection within the optical element (8) in the first transformation segment (10) and being bundled in a peak region of the output light intensity distribution, and at least one further transformation segment (20, 30), with the light from the light source experiencing refraction only in the at least one further transformation segment (20, 30).

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.

An exterior light unit, has an LED in operation emitting light; a reflector, which reflects a first portion of the light emitted by the LED; a first lens, through which the first portion of the light is refracted after being reflected by the reflector; and a second lens, which is an aspherical collimating lens and which is arranged in such a way with respect to the LED that a second portion of the light emitted by the LED has an unobstructed path to the second lens and is collimated by the second lens in a main light output plane. The second portion of the light, when on its way from the LED to the second lens, crosses way with the first portion of the light, when on its way from the reflector to the first lens.