Abstract:
An aircraft LED light unit comprises at least one printed circuit board which comprises at least one metal core layer and at least one dielectric layer, and at least one LED disposed on the printed circuit board and which comprises an anode and a cathode for electrically coupling to a power source. One of the anode and cathode of the at least one LED is connected to an electrical conductor which is disposed on the dielectric layer and is coupled to a first terminal of the power source, wherein the dielectric layer electrically isolates the electrical conductor from the metal core layer, and the other one of the anode and cathode of the at least one LED is connected to the metal core layer of the at least one printed circuit board, wherein the metal core layer is coupled to a second terminal of the power source.
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:
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 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:
Aircraft headlight includes at least one light source; and a light transmissive cover, at least partially covering the at least one light source. The light transmissive cover includes a first layer made of a first material; a second layer made of a second material, which differs from the first material; and at least one electric heating wire for heating the light transmissive cover by passing an electric current through the electric heating wire. The at least one electric heating wire is embedded into the first layer.
Abstract:
An aircraft beacon light with integrated health monitoring comprises an annular arrangement of light sources, which are configured for repeatedly emitting beacon light flashes; a light detection sensor surrounded by the annular arrangement of light sources; and at least one reflective portion arranged to reflect light emitted by the annular arrangement of light sources onto the light detection sensor.
Abstract:
An aircraft beacon light with integrated health monitoring comprises an annular arrangement of light sources, which are configured for repeatedly emitting beacon light flashes; a light detection sensor surrounded by the annular arrangement of light sources; and at least one reflective portion arranged to reflect light emitted by the annular arrangement of light sources onto the light detection sensor.
Abstract:
An electric aircraft emergency power supply module includes at least one electric power cell for storing and supplying electric energy and a controller for controlling charging and discharging of the at least one electric power cell and for determining a charging level of the at least one electric power cell. The controller includes a simulator, which is configured for simulating an electric behavior of at least one temperature sensitive element as a function of the charging level of the at least one electric power cell.
Abstract:
A combined aircraft navigation and anti-collision light, includes: at least one navigation light source and one anti-collision light source; a navigation light sensor, in operation outputting a light detection signal corresponding to an amount of light detected by the navigation light sensor; first and second optical systems, associated with navigation and collision light sources, wherein the first optical system is configured for shaping a navigation light output from light emitted by the at least one navigation light source and is configured for directing stray light from the at least one navigation light source to the navigation light sensor and a second optical system, associated with the at least one anti-collision light source and configured for shaping an anti-collision light output from light emitted by the at least one anti-collision light source; a lens cover, arranged over the light sources and optical systems for passing light therethrough.
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.