Goodrich Lighting Systems Gmbh

Hella Kg Hueck and Co.

Sascha Lueder

Anil Kumar Jha

Andre Hessling Von Heimendahl

Christian Schoen

Franz-Josef Beermann

Andre Hessling-Von Heimendahl

Frank Klein

Rico Schulz

Ramesh Srinivasamurthy

Frank Gronemeier

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&#xb0; in a first cross-sectional plane, and a second light emission opening angle of at most 180&#xb0; 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&#xb0; both above and below the second cross-sectional plane.

Aircraft beacon light unit and set of aircraft beacon light units

A drain valve for draining liquid from an enclosed space comprises a movable plunger, which is movable between a closed position in which the plunger does not allow liquid to flow through the drain valve, and at least one open position, in which the plunger allows liquid to flow through the drain valve; and an elastic element, which is configured to urge the movable plunger into its closed position. The plunger is provided with at least one duct extending through the plunger and allowing fluid to flow through the drain valve when the plunger is positioned in its closed position, wherein said at least one duct is closed by a semi-permeable medium, which is permeable for air and water vapor and impermeable for liquid water.

Drain valve, exterior aircraft light unit and power supply box

An aircraft vertical stabilizer illumination light unit, configured for being arranged in a rotatable horizontal stabilizer of an aircraft and for being oriented towards a vertical stabilizer of the aircraft for illuminating the vertical stabilizer, includes an LED group, having a plurality of LEDs, and an optical system, having at least one optical element, the optical system being associated with the LED group for shaping an output light intensity distribution from the light emitted by the LED group.

Aircraft vertical stabilizer illumination light unit and method of operating an aircraft vertical stabilizer illumination light unit

An exterior aircraft light unit includes a mounting structure, an LED arranged on the mounting structure, and an optical system, arranged on the mounting structure for creating an output light emission distribution of the exterior aircraft light unit. The optical system has, in a first cross-sectional plane extending through the LED, a first concave reflector and a second concave reflector, each of the first and second concave reflectors having a proximate end positioned adjacent to the mounting structure and a distal end positioned removed from the mounting structure, with the first and second concave reflectors being arranged on opposite sides of the LED in the first cross-sectional plane, and a refractive optical element arranged between the first and second concave reflectors in the first cross-sectional plane. The distal ends of both the first and second concave reflectors that curve towards each other and have back-tapered shapes.

Exterior aircraft light unit and aircraft comprising the same

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.

A combined wing scan and winglet illumination light unit is disclosed. The light unit has at least one LED and at least one optical structure for shaping a light emission distribution of the combined wing scan and winglet illumination light unit. The wherein the light emission distribution has a first illumination region for illuminating a wing and a wing engine of an aircraft and a second illumination region for illuminating a wing tip winglet of the aircraft.

Combined wing scan and winglet illumination light unit and aircraft having winglet illumination

A lamp, in particular a position lamp for a motor vehicle, has a housing in which at least one light source is arranged, with the housing having a light pane covering an opening of the housing, with the light source being structured as a plurality of light-emitting diodes. A light field formed by a plurality of similar first light-emitting diodes to produce a basic light-intensity distribution and at least one additional second light-emitting diode to produce a preferred light-intensity distribution is provided so that a predetermined total light-intensity distribution is obtained by superpositioning, or overlapping, of the basic light-intensity distribution and the preferred light-intensity distribution.

Growing community of inventors

Rietberg, Germany

Sascha Lueder