Abstract: An aircraft interior light unit having a light output over an extended light emission area includes a flat light distribution body having a front surface, through which the light output is coupled out, and a back surface, wherein at least one of the front surface and the back surface of the flat light distribution body has a plurality of surface irregularities.

Abstract: 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.

Abstract: An aircraft landing light unit includes a plurality of LEDs, an optical system associated with the plurality of LEDs for shaping a light output of the aircraft landing light unit for illuminating an aircraft environment, a control unit for controlling the plurality of LEDs, and a photo detector arranged for detecting light, emitted by the plurality of LEDs, output via the optical system and reflected by atmospheric haze, such as clouds, fog, rain and snow, wherein the control unit is coupled to the photo detector and is configured to control the plurality of LEDs on the basis of the light detected by the photo detector, thereby adjusting the light output of the aircraft landing light unit to the atmospheric haze.

Abstract: An exterior aircraft light unit for emitting light of a first wavelength and light of a second wavelength, different from the first wavelength is disclosed. The exterior aircraft light unit has an integrated optical structure, which in turn has a first light source configured to emit the light of the first wavelength, a second light source configured to emit the light of the second wavelength, the second light source being positioned adjacent to the first light source, and an optical element for shaping a light emission distribution of the integrated optical structure. The optical element is arranged with respect to the first light source and the second light source in such a way that it affects both the light of the first wavelength and the light of the second wavelength.

Abstract: An aircraft LED light unit is disclosed that includes a flat electric circuit device having a first main surface, a second main surface and at least one side surface extending between the first main surface and the second main surface, power supply circuitry, disposed in the electric circuit device, at least one heat transport element, disposed in the electric circuit device, and at least one LED. The at least one LED is arranged on the at least one side surface of the electric circuit device, is electrically coupled to the power supply circuitry, and is in heat exchange relationship with the at least one heat transport element.

Abstract: A combined anti-collision and navigation light unit for an aircraft includes a light source, having at least one LED and having a source-side light intensity distribution, and a lens cover with a shape that is configured to transform the source-side light intensity distribution into an output light intensity distribution of the combined anti-collision and navigation light unit.

Abstract: An emergency lighting system for an aircraft includes an emergency light control unit, having an external power input and at least one external control input for receiving external control commands from at least one of a cockpit crew, a cabin crew, a board computer and an autopilot, and a plurality of autonomous emergency light units, each of the plurality of autonomous emergency light units comprising at least one LED and a rechargeable capacitor. The emergency light control unit is configured to process the external control commands and to communicate emergency light control commands to the plurality of autonomous emergency light units as a response to the external control commands.

Abstract: A dynamic exterior aircraft light unit includes a plurality of LEDs, with at least two subsets of the plurality of LEDs being separately, an optical system for transforming light output from the plurality of LEDs into at least two light emission distributions, a control unit for controlling the plurality of LEDs, and a photo detector arranged to detect light, emitted by the dynamic exterior aircraft light unit as part of the at least two light emission distributions and reflected by the aircraft environment, and configured to output a light detection signal.

Abstract: A method for controlling a mechanical vibrating element driven by a driving means includes operating the driving means at an operation frequency for stimulating the vibrating element to oscillate at this frequency. The method also includes adjusting the operation frequency of the driving means for stimulating the vibration element at different frequencies and of determining a respective energy consumption of the driving means depending on the frequency at which the vibrating element oscillates. The resonance frequency of the oscillation of the vibrating element is identified as the frequency at which the energy consumption of the driving means is lowest and the driving means for stimulating the vibrating element can be operated at the resonance frequency.

Abstract: A dimmable LED reading light unit includes a dimming module and an LED module, connected in series. The dimming module has an input being connectable to a power supply supplying direct voltage and includes a potentiometer allowing section of a dimming rate and a current controller providing an operating current for the LED module. The LED module includes at least one LED and a current consumer connected in parallel and the current controller is configured to supply direct current to the LED module that substantially corresponds to the sum of the driving current necessary for driving the at least one LED to emit light with an intensity of illumination corresponding to the dimming rate of the potentiometer, and the current consumption of the current consumer.

Abstract: An autonomous emergency light unit for an aircraft has a power input for receiving power from an external power supply, a rechargeable power source, at least one LED for illuminating the emergency light unit, and a light unit control logic configured to operate the emergency light unit in a plurality of operating states as a response to external control information received and processed by the light unit control logic. The plurality of operating states includes a discharge and illumination state, with the rechargeable power source being discharged over the at least one LED in the discharge and illumination state. The light unit control logic is configured to operate the emergency light unit in the discharge and illumination state as a response to no power being provided at the power input.

Abstract: A multi-color light unit includes a plurality of lighting circuits, with each lighting circuit being coupled to a joint power terminal. The plurality of lighting circuits include a first lighting circuit, which includes a first current source, coupled to the joint power terminal, a plurality of first LED's, in operation emitting light of a first color, and a plurality of voltage drop diodes, in operation not emitting light, the plurality of first LED's and the plurality of voltage drop diodes being coupled to the first current source. The plurality of lighting circuits further include a second lighting circuit, which includes a second current source, coupled to the joint power terminal, and a plurality of second LED's, in operation emitting light of a second color, the plurality of second LED's being coupled to the second current source. The first current source and the second current source are of equal design.

Abstract: 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.

Abstract: An LED light unit, in particular for a passenger transport vehicle, such as an aircraft, a road vehicle, a ship or a rail car, is disclosed that has at least one LED and is configured to be used with a high intensity discharge lamp power supply that is adapted to monitor its output behavior. The LED light unit comprises a power input coupleable to the high intensity discharge lamp power supply, a capacitor switchably coupled to the power input for absorbing electrical energy from the high intensity discharge lamp power supply, and a power dissipating element switchably coupled to the power input for dissipating electrical energy from the high intensity discharge lamp power supply.

Abstract: 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.

Abstract: The invention comprises a method for indicating that an LED flash light for an aircraft such as an anti-collision or beacon or strobe LED light has reached a near-end-of-life status, wherein the LED flash light under normal operational condition within a given time interval generates a predetermined number of normal flashes with the number being one or more than one, e.g. two. The method comprises the steps of determining the actual photometric condition of the LED flash light, and comparing the actual photometric condition to a given condition in a normal flashing mode. If the actual condition deviates from the given condition by more than a predetermined amount, the LED flash light is operated in order to generate within the given time interval one additional near-end-of-life-indicating flash.

Abstract: An LED reading light, in particular for a passenger transport vehicle, such as an aircraft, a road vehicle, a ship or a rail car, is disclosed that has a plurality of illuminating LED's and in operation provides a desired light intensity for a set supply current, wherein the LED reading light comprises two power supply terminals connectable to a power supply for receiving the set supply current, and at least one lighting strand coupled between the two power supply terminals. Each of the at least one lighting strand comprises at least one voltage drop diode, with the at least one voltage drop diode in operation not contributing to the desired light intensity, and at least one of the illuminating LED's. The illuminating LED's are distributed among the at least one lighting strand and connected such that they jointly provide the desired light intensity for the set supply current.

Abstract: A dimmable LED reading light unit, in particular for a passenger transportation vehicle, such as an airplane, a bus or a ship, comprises an input which is connectable to a potentiometer that outputs a direct voltage having a voltage intensity corresponding to a selected potentiometer position; a load current source being configured to generate a predetermined load current; a current controller providing an operating current for operating at least one LED; and an electronic measuring and control unit; wherein the load current source and the current controller are connected to the input in parallel.

Abstract: An aircraft light comprises a housing (24), at least one light source (32) to be cooled, the at least one light source (32) being arranged in the housing (24), a heat sink element (26) thermally coupled to the at least one light source (32) and defining a cooling surface (36) exposable to a cooling airstream (52) for the cooling airstream (52) to flow along the cooling surface (36) in a flow direction. The cooling surface (36) extends between upstream and downstream end portions (40,42) spaced apart in the flow direction and means for generating a pressure difference between the upstream and downstream end portions (40,42) of the cooling surface. Due to the pressure difference, a cooling airstream (52) flowing along the cooling surface (36) is created.

Abstract: Aerospace ground maneuver light, comprises a reflector (14), the reflector (14) defining a light exit plane (18), an LED light source (26) arranged outside of the area defined by the reflector (14) and its light exit plane (18), and a mounting bar (22) which has a longitudinal extension and at which the LED light source (26) is mounted. The mounting bar (22) extends across the reflector (14) and is spaced apart from the light exit plane (18) of the reflector (14) and comprises a mounting side (24) facing towards the reflector (14) and its light exit plane (18), with the LED light source (26) arranged on the mounting side (24) for emitting light towards the reflector (14).