Abstract: A light device comprises an elongated light guide (2) and a LED source (1) seated in the light guide entry part (3) for emitting the light beam into the light guide (2). The entry part of the light guide comprises mutually intersecting parts of at least two ellipsoids (11, 21) arranged with their main axes (14, 24) next to each other. The LED light sources are fitted in the first focuses (15, 25) of the ellipsoids for emission of light beams and their reflection from the elliptic walls (13, 23) thereof to the second focuses (16, 26) thereof, laying inside the light guide in different distances from the first focuses. The distance between the first focus (15) and the second focus (16) of the first ellipsoid (11) preferably equals at least 1.5 times the distance between the first focus (25) and the second focus (26) of the second ellipsoid (21).

Abstract: A system and method for estimating a distance between an aircraft and an object is disclosed. An exterior light of the aircraft transmit a test light signal and a parameter the transmitted test light signal is measured. A sensor receives a reflection of the test light signal from the object and the parameter is measured for the reflection test signal. The distance between the aircraft and the object is estimated using the parameter of the reflection and the parameter of the test light signal. The exterior light is generally a light that is built into the aircraft during aircraft construction while the sensor is retrofitted onto the aircraft.

Abstract: In an embodiment, a layer material configured to be arranged on a rotor blade tip of a helicopter comprises at least one light emitting or reflecting section that emits or reflects light after being exposed to a remote light source. The light source can be arranged on the body of the helicopter.

Abstract: A dual mode light assembly for a forward position light of an aircraft includes a base, a visible light source mounted to the base that is configured to emit visible light, a covert light source mounted to the base that is configured to emit covert light, and a light shield mounted to the base. The light shield is configured to restrict transmission of the visible light to a visible light pattern and to restrict transmission of the covert light to a covert light pattern.

Abstract: An exterior helicopter light unit (2) with a dynamic output light intensity distribution includes a plurality of LEDs (30), and an optical system (32) for shaping the output light intensity distribution from light emitted by the plurality of LEDs (30), wherein each of the plurality of LEDs (30) contributes to the output light intensity distribution in an LED-specific output direction region, wherein at least a portion of the plurality of LEDs (30) are individually dimmable, with a level of dimming for each of said portion of the plurality of LEDs (30) in operation being set depending on a distance of the exterior helicopter light unit (2) to ground (200) in the respective LED-specific output direction region.

Abstract: An interior aircraft light unit includes at least one light source, in operation emitting light with a source side light intensity distribution, the source side light intensity distribution having a first intensity region and a second intensity region, with the first intensity region having a higher light intensity than the second intensity region, and a semi-transparent layer, disposed between the at least one light source and an outside of the interior aircraft light unit, for transforming the source side light intensity distribution into an adjusted light intensity distribution, wherein the semi-transparent layer has a transparency distribution having a lower degree of transparency in the first intensity region than in the second intensity region, such that the adjusted light intensity distribution is closer to an even light intensity distribution than the source side light intensity distribution.

Abstract: In a lighting system that emits light of a color within a color specification, the color is controlled by adding light from a single color-correcting light emitting device (light-emitting device) to a primary light-emitting device. In an illustrative embodiment, a color-detecting module can sense the color of the combined light emitted from both the primary and the color-correcting light-emitting devices. The color-control system can generate an amplitude control signal based on a signal indicative of the color sensed by the color-detecting module. A color range of the combined light of the primary and the color-correcting light-emitting devices can intersect a domain of the predetermined color specification, as the generated amplitude control signal spans the domain. Using a single color-correcting light-emitting device to maintain a lighting system's emitted color within a predetermined color specification can advantageously reduce system complexity.

Abstract: A rotorcraft winch lighting device, which is attachable to a rotorcraft winch, mounted to a rotorcraft such as a helicopter, the rotorcraft winch including a stationary portion and a mobile portion which is movable with respect to the stationary portion, includes: a stationary unit including a stationary coil and a mobile unit. The mobile unit is movable with respect to the stationary unit and includes at least one light source, at least one electrical storage device, and at least one mobile coil, which is electrically connected to the electrical storage device and/or the at least one light source. The stationary coil and the mobile coil are configured for transferring electrical energy from the stationary unit to the mobile unit when the at least one mobile coil is positioned in an energy transfer position in the vicinity of the at least one stationary coil.

Abstract: A light device, especially a headlight of motor vehicles, comprises at least one light unit (1), or a group (1a, 1b) of light units, at least one optical directing element (3, 2e, 3f), adapted to direct the light beam emitted by the light unit, or group of light units, to the required direction, and at least one output lens (4) for passage of at least a part of the light rays of the light beam or beams to create a light pattern (A, B, C) on the display surface (ZY). On the route of the light beam between the optical directing element and the output lens, there is at least one optical diaphragm element (11, 21, 31) containing a system of trim edges (13, 23, 33) to create the required shape of the cross-section of a part or parts of the light beam designed for transmission along the above-mentioned route.

Abstract: A light device comprises at least one light source (10) to generate light rays (201, 202, 203), an output lens (5), and lateral walls (7, 8) delimiting a space (27) for passage of the light rays after the lens and exiting out of the light device through a transparent cover (9) covering the space at the front. Between the light source and the output lens, a reflective diaphragm (11) is arranged that comprises fixed reflective lateral walls (11a, 11b), for spatial delimitation of the light rays between the lateral walls before they enter the output lens. The output lens has, in the vertical direction at the side facing the diaphragm, a convex shape and the lateral walls include, at the side facing the output lens, free ends (14) that have a rounded concave shape in the vertical direction, which is substantially complementary to the output lens convex shape.

Abstract: An interior aircraft LED light unit includes at least one printed circuit board, on which a plurality of LEDs are connected to a power source, each one of the plurality of LEDs having a predetermined distance to the power source, and each one of the plurality of LEDs being associated with a respective thermal transfer member having a predetermined size, for transferring heat away from the respective LED, wherein, for at least some of the plurality of LEDs the predetermined size of the respective thermal transfer member varies with the predetermined distance of the LED to the power source.

Abstract: An LED light system for an aircraft may comprise a first LED lamp having a first LED array. The first LED array may include at least a first LED and a second LED. A first optical element may be configured to direct light emitted from the first LED in a first beam centered around a first angle and to direct light emitted from the second LED in a second beam centered around a second angle. The LED light system may further comprise a second LED lamp having a second LED array. The second LED array may include at least a third LED and a fourth LED. A second optical element may be configured to direct light emitted from the third LED in a third beam centered around the first angle and to direct light emitted from the fourth LED in a fourth beam centered around the second angle.

Abstract: An exterior aircraft light unit includes a plurality of LEDs; a support plate for supporting the plurality of LEDs, the support plate having a main plane of extension, wherein the support plate has a curved, concave LED support surface, substantially orthogonal to the main plane of extension, and wherein the plurality of LEDs are arranged along the curved, concave LED support surface; and a reflector, facing the plurality of LEDs and shaped to reflect light from the plurality of LEDs past the support plate towards an outside of the exterior aircraft light unit.

Abstract: An LED light unit comprises a support portion, a light source having at least one LED, the light source being arranged on the support portion and having a source-side light intensity distribution (LISS), and a refractive optical element having an inner surface and an outer surface, with at least one of the inner surface and the outer surface being non-spherical, the refractive optical element being arranged over the light source and being attached to the support portion.

Abstract: An LED light unit, in particular for a passenger transportation vehicle, such as an aircraft, a road vehicle, a ship or a rail car, has a support portion a light source having at least one LED, the light source being arranged on the support portion, and a refractive optical element having an inner surface and an outer surface the refractive optical element being attached to the support portion and being arranged over the light source. The refractive optical element has a chamfer portion adjacent the support portion, wherein at least one of the inner surface and the outer surface has at least one chamfer surface in the chamfer portion.

Abstract: A self-checking emergency light unit includes a power input terminal coupleable to an external power supply for receiving power therefrom, an illumination circuit coupled to the power input terminal, a discharge circuit coupled to the emergency power source, and an operational check module coupled to the emergency power source.

Abstract: A device for forming a dynamic image on an aircraft sign includes a plurality of light sources, an input power line, a first timer and a second timer both connected to an enable input and a plurality of delay circuits each connected to a different one of the light sources. The system also includes a counter having a plurality of counter outputs, the counter receiving a counting pulse from the first timer in a dynamic mode of operation and disable signal from the second timer after expiration of a preset time, the expiration of the preset time causing the device to transfer from the dynamic mode to a static mode where each of the plurality of light sources are simultaneously illuminated.

Abstract: A dynamic aircraft headlight, includes an LED group, having a plurality of LEDs, and an optical system, comprising at least one optical element, for shaping an output light intensity distribution from the light emitted by the LED group. The LED group and the optical system are stationary within the dynamic aircraft light unit, with each LED of the LED group has a set position with respect to the optical system and with a light output of each LED being affected differently by the optical system.

Abstract: A lighting system for automobiles is proposed which includes a laser light source emitting a primary laser light bundle within a solid angle area around a beam direction, a photoluminescence element positioned within the emitted primary light beam, and a protective element that protects against stray laser rays. The photoluminescence element is configured to absorb the laser rays impinging on said element and by means of the photoluminescence to radiate secondary light rays. The lighting system includes a protection system with a protective element of an elongated shape having a first end and a second end, wherein the first end of the protective element is positioned within the beam direction of the primary light beam and downstream of the photoluminescence element.

Abstract: A light emitting apparatus and lighting fixture including a plurality of light emitting sub assemblies, each sub assembly comprising a plurality of LEDs. At least one light emitting subassembly comprises a diffuser positioned in front of a light emitting side of the LEDs on the subassembly. At least one of the other light emitting subassembly comprises a reflector reflecting light emitted from the LEDs.