Goodrich Lighting Systems Gmbh

Other

Airbus Operations Gmbh

Airbus Deutschland Gmbh

Andre Hessling

Martin Griesbach

Anil Kumar Jha

Sascha Lüder

Sonja Ferling

Enrico Beier

Christian Riedel

Christian Schoen

Carsten Kohlmeier-Beckmann

Norbert Menne

Roderich Thometschek

Siegfried Schmees

Stefan Thomassin

Robert Trinscheck

Bruno Jansa

Alexander Wernicke

Claus-Dieter Meissner

Mike Herberhold

Christian Schön

Benjamin Willeke

Bernhard Müller

An aircraft light comprises a housing, at least one light source to be cooled, the at least one light source being arranged in the housing, a heat sink element thermally coupled to the at least one light source and defining a cooling surface exposable to a cooling airstream for the cooling airstream to flow along the cooling surface in a flow direction. The cooling surface extends between upstream and downstream end portions spaced apart in the flow direction and means for generating a pressure difference between the upstream and downstream end portions of the cooling surface. Due to the pressure difference, a cooling airstream flowing along the cooling surface is created.

Aircraft light

A strobe light unit, particularly wing anti-collision strobe light unit for an aircraft, comprises at least one light source, particularly at least one LED; a reflector element, the at least one light source and the reflector element being configured for projecting light into a desired range of directions; and a stray light blocking element for blocking stray light from being projected into undesired directions, the stray light blocking element attached to the reflector element or to a base portion of the strobe light unit.

Strobe light unit and aircraft comprising the same

A light for an aircraft comprises a holder for carrying a first group of light emitting diodes arranged along a curvilinear line and a first reflector having an elliptic reflective partial surface defining a plurality of focal points forming a first curvilinear focal line coinciding with the light emitting sites of the first group of light emitting diodes and second focal point or curvilinear focal line. The light further includes a second optical unit comprising a single further focal point or curvilinear focal line that coincides with the second focal point or focal line of the first reflector. The light further includes a second group of light emitting diodes displaced axially with respect to the first light emitting diodes, which emit light that bypasses the second focal point or focal line of the first reflector of the first optical unit.

Light for an aircraft

An aircraft light comprises a housing (), at least one light source () to be cooled, the at least one light source () being arranged in the housing (), a heat sink element () thermally coupled to the at least one light source () and defining a cooling surface () exposable to a cooling airstream () for the cooling airstream () to flow along the cooling surface () in a flow direction. The cooling surface () extends between upstream and downstream end portions () spaced apart in the flow direction and means for generating a pressure difference between the upstream and downstream end portions () of the cooling surface. Due to the pressure difference, a cooling airstream () flowing along the cooling surface () is created.

An aircraft light for emitting light in a desired spatial angular region and with a desired light distribution, comprises a reflector having an upper reflector portion and a lower reflector portion both being symmetrical to a plane. A first row of LEDs are face away from the reflector. A second row of LEDs face towards the reflector. Each of the upper and lower portions of the reflector comprises first, second, and third reflective surfaces with the first reflective surface being convexly shaped, the second reflective surface being substantially flat, and the third reflective surface being partially parabolically shaped.

Aircraft light for emitting light in a desired spatial angular region and with a desired light distribution

A method for controlling an aircraft having a plurality of LEDs, light so as to emit a desired light intensity includes the steps of providing a reference LED located within or outside of the aircraft light, providing thermal conditions resulting in a thermal stress for the reference LED similar to the maximum thermal stress, and observing the reference LED by means of an optical sensor for monitoring the optical aging behavior of the reference LED throughout its lifetime. The desired light intensity of the aircraft light is achieved by controlling the plurality of LEDs in accordance with the monitored aging behavior of the reference LED.

Method for controlling an aircraft light

An aircraft light consists of a housing containing a light source, a heat sink element forming at least part of the exterior surface of the housing and an auxiliary thermal capacitor that is thermally decoupled from the heat sink element. A thermally expandable medium is coupled to the heat sink element and operates to thermally decouple the light source from the heat sink element and thermally couple the light source to the auxiliary thermal capacitor and vice versa, depending on the actual temperature of the heat sink element.

An integrated aircraft landing and taxi light includes upper and lower reflector regions in the shape of substantially circular segments and a central longitudinal third reflector region extending between the upper and lower reflector regions. Landing light LEDs are arranged within the upper and lower reflector regions and the outer portions of the central longitudinal reflector region with the diagonals of the LED dies oriented substantially along radial lines extending outward from the center of the light. Taxi light LEDs are arranged within the central and outer portions of the central longitudinal reflector region such that the sides of the LED dies are oriented substantially horizontally and vertically with respect to the aircraft.

Combined aircraft landing and taxi light

An anti-collision aircraft light comprises at least one LED and a control unit for operating the at least one LED in a pulsed manner. In this anti-collision aircraft light, the control unit comprises an ambient temperature sensor for sensing the ambient temperature and an adjustable current control for setting an LED operating current depending on the sensed ambient temperature. The control unit further includes a light intensity sensor for sensing the intensity of the light emitted from the at least one LED, an integrator connected to the light sensor for integrating the sensed light intensity, and a comparator for comparing the integrated light intensity to a threshold value. The operating current for the at least one LED is interrupted as soon as the integrated light intensity is equal to the threshold value.

Anti-collision aircraft light

A light for an aircraft comprises a holder for carrying a plurality of light emitting diodes arranged along a curvilinear line and a first optical unit comprising an elliptic reflective partial surface defining a plurality of focal points forming a first curvilinear focal line extending along the light emitting sites of the light emitting diodes, and a plurality of second focal points. The light further includes a second optical unit comprising a single further focal point or a plurality of further focal points forming a further curvilinear focal line. The plurality of the second focal points of the first optical unit coincide and are identical to the single further focal point of the second optical unit or are located along the further curvilinear focal line of the second optical unit.

An LED landing light arrangement for an aircraft comprises a plurality of LED light sources () for arrangement on an aircraft (), primarily on the wing roots (), on the front edges of the wings () and/or on the landing gears (). The LED light sources () are operative to generate, relative to the central axis of the aircraft (), a light distribution () ahead of the aircraft () that is spread substantially in a Y-shaped configuration in an obliquely downward direction. The light distribution () comprises two converging lateral regions () arranged laterally ahead of the aircraft (), and a central region () running from said converging lateral regions () along an extension of said central axis and oriented in a direction away from the aircraft ().

LED landing light arrangement for an aircraft

The warning lamp for an aircraft is provided with a housing () which possesses a light permeable cover () that is exposed to the surrounding air when the housing is mounted on the aircraft, with a frontal cover area and a rear cover area, a mounting element () to fasten the cover to a lower part () of the housing (), wherein one edge () of the cover () is covered by an edge of the mounting element () and protrudes from it, a lamp with at least one LED (), which is arranged within an area that is covered by the cover (), and a cooling body () for the at least one LED (), wherein the cooling body () possesses a cooling surface () that is exposed to the surrounding air when the housing () is mounted on the aircraft. The frontal cover area is formed by a frontal cover element () which is made from a light permeable first material. The rear cover area is formed by a rear cover element (), which is made from a light permeable second material. The cooling body (), while separating the frontal cover element () from the rear cover element (), is arranged between them, wherein its cooling surface () is a part of the external contours of the cover () of the housing () that is given by the frontal and rear cover elements () and possesses an upper region () as well as adjacent, opposing side areas ().

Warning lamp for an aircraft

The invention relates to an LED light, particularly a reading or seat lamp for vehicles such as travel coaches or airplanes, said light being equipped with a housing (), a plurality of LEDs comprising first LEDs () that transmit electromagnetic radiation in a first wavelength range, and an activation unit () for activating the first LEDs (). The LED light further comprises a conversion material () that, upon excitation by at least part of the electromagnetic radiation from the first LEDs (), emits electromagnetic radiation in a conversion wavelength range that is in the visible spectrum range and is at least partially different from the first wavelength range. The LEDs further comprise second LEDs () that, in order to shift the color of the electromagnetic radiation emitted by the conversion material () upon excitation by the electromagnetic radiation emitted by the first LEDs (), emit electromagnetic radiation in a second wavelength range. The second LEDs () may be selectively activated by the activation unit () in addition to the first LEDs (), wherein the electromagnetic radiation from the second LEDs () is at least partially in the visible spectrum range and is at least partially different from the wavelength range of the first LEDs () and passes the conversion material () substantially without exciting said conversion material and/or wherein the electromagnetic radiation of the second LEDs () additionally excites the conversion material () to emit electromagnetic radiation, the wavelength range of which is inside or outside of the conversion wavelength range.

Color-variable LED light, particularly for lighting the interior of vehicles

The method for assembly of an LED lighting device comprising an LED module and a reflective and/or refractive optical unit and provided particularly as a reading or seat light for use in a vehicle such as, e.g., an airplane, a train or a bus, comprises the following steps:

Method for assembly of an LED light

A device is provided for fastening a first part to a stationary second part, in particular to a part of a vehicle, having a fastening element which can be connected to the first part and has at least one locking element arranged so it cannot be lost, such that it can be brought into a locked position where the first part is joined to the second part and it can also be brought into an unlocked position where the first part is released from the second part, where the fastening element has a top part facing the second part and a bottom part facing the first part, where the top part and the bottom part are designed to pivot about a pivot axis, and the locking element is mounted on the top part.

Growing community of inventors

Koblenz, Germany

Andre Hessling