Abstract: A networked infrastructure is described that includes a set of programmed computing nodes, each node being configured with a processor and non-transitory computer readable media including computer-executable instructions that, when executed by the processor, facilitate a social security number registry server carrying out a method that provides an individual with the ability to remotely approve or disapprove, in real-time, the use of his/her social security number (SSN) by a relying party server.

Abstract: A helicopter search light includes a movable light head comprising: at least one light source and at least one optical element, which are configured for emitting a search light beam; at least two radiation sensors arranged in a preset distance (d) from each other. The radiation sensors are configured for detecting electromagnetic radiation and providing corresponding sensor signals. The system also includes an image processing module configured for receiving the sensor signals provided by the at least two radiation sensors and generating enhanced image data from said sensor signals and a controller configured for controlling movement of the movable light head depending on said enhanced image data.

Abstract: A lighting assembly is provided with a housing defining a cavity that is aligned along a longitudinal axis. A light source is supported by the housing and aligned with the longitudinal axis. A lens is supported by the housing to collimate light from the light source. An image plate with a plurality of apertures formed through passes a portion of the collimated light as light segments. An exit lens includes a first series of optics arranged on a first plane spaced apart from the image plate at a first focal distance to focus the light segments at a first distance from the housing, and a second series of optics arranged on a second plane spaced apart from the image plate at a second focal distance to focus the light segments at a second distance from the housing. The second focal distance is greater than the first focal distance.

Abstract: Systems and methods for deicing an aircraft landing light may include a metal mesh conductor coupled to a lens of a landing light. The systems and methods may include a power supply, a temperature sensor, a deicing control unit, an aircraft light having a lens, and a mesh coupled to the lens. The temperature sensor may be a microwave resonator sensor configured to sense the temperature of the landing light and send signals to the deicing control unit. The signals may be configured to instruct the deicing control unit to either apply an electric current to the mesh, or cease applying an electric current to the mesh, depending on the landing light temperatures. The deicing control unit may receive landing pulses from a flight control system. The pulses may indicate that the aircraft is landing or has landed.

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 interior aircraft light includes a mounting structure for mounting the interior aircraft light to an aircraft seat; a UV radiation source; and an optical system, configured to direct UV radiation from the UV radiation source towards a floor portion underneath the aircraft seat.

Abstract: An aircraft passenger reading light comprises at least one reading light source, which is arranged for emitting visible light in a reading light emission direction; and at least one infrared light source, which is arranged for emitting infrared light in an infrared light emission direction. The infrared light emission direction is inclined with respect to the reading light emission direction.

Abstract: A monitoring circuit and a method for function monitoring is disclosed where the device includes the input being connected with a first subassembly that detects a frequency range of the status signal, with the first subassembly being connected with a second subassembly to implement a logical signal combination. The second subassembly is connected with a third subassembly generating a delayed output signal. The method compares a frequency fsw of the status signal with a lower first cutoff frequency f1 and an upper second cutoff frequency f2. When the frequency fsw of the status signal is located within the predetermined frequency range, the functional reliability signal is provided with a first voltage level, and when the frequency fsw of the status signal is located outside of the predetermined frequency range, the functional reliability signal is provided with a second voltage level that is different from the first voltage level.

Abstract: A nonlinear converter may comprise: alternating layers of a dielectric material and a metal material; a first refractive index of the nonlinear converter for a first wavelength (i.e., input wavelength or pump wavelength) between 207 nm and 237 nm, the first refractive index being less than 0.5, the first refractive index corresponding to metal fill ratio; and a second refractive index of the nonlinear converter for a second wavelength (i.e., output wavelength or SHG wavelength), the second wavelength being approximately double the first wavelength, the second refractive index corresponding to the metal fill ratio.

Abstract: The light-guiding optical unit (1) for a light device of motor vehicles comprises a light guide (2) that comprises at least one routing surface (3), and at least one light source (4) to generate light rays (10). The light-guide (2) further comprises a top surface (12) at least a part of which is constituted by the output surface (15), and a bottom surface (13) opposite the top surface (12) and fitted with a prismatic structure (16) comprising reflective surfaces (7).

Abstract: A flight direction indication system for an aerial vehicle having a plurality of rotors includes: for each of the plurality of rotors, at least one rotor blade having a plurality of light sources arranged along a radial extension of the rotor blade; and a control unit, coupled to the plurality of light sources of the rotor blades of the plurality of rotors. The control unit is configured to effect a coordinated control of the plurality of light sources of the rotor blades of the plurality of rotors, with the coordinated control yielding an image or a sequence of images across the plurality of rotors to an observer of the aerial vehicle and to to control the plurality of light sources of the rotor blades of the plurality of rotors on the basis of a momentary flight direction of the aerial vehicle.

Abstract: A lighting assembly is provided with a housing defining a cavity that is aligned along a longitudinal axis. A light source is supported by the housing and aligned with the longitudinal axis. A lens is supported by the housing to collimate light from the light source. An image plate with a plurality of apertures formed through passes a portion of the collimated light as light segments. An exit lens includes a first series of optics arranged on a first plane spaced apart from the image plate at a first focal distance to focus the light segments at a first distance from the housing, and a second series of optics arranged on a second plane spaced apart from the image plate at a second focal distance to focus the light segments at a second distance from the housing. The second focal distance is greater than the first focal distance.

Abstract: An exterior aircraft light cover with integrated illumination includes a mounting portion, configured to be mounted to an exterior aircraft light housing; a light transmissive pane, supported by the mounting portion. The mounting portion and the light transmissive pane are configured to jointly close the exterior aircraft light housing. The cover also includes at least one photovoltaic device, which is configured for generating electric energy when illuminated; at least one electric storage device, which is configured for storing the electric energy generated by the at least one photovoltaic device; and at least one ancillary light source, which is operable with electric energy supplied by at least one of the at least one photovoltaic device and the at least one electric storage device.

Abstract: Rotorcraft lighting equipment includes a plurality of lighting devices configured to be mounted to an exterior of a rotorcraft, wherein each of the lighting devices comprises a plurality of individually controllable lighting modules which are configured for emitting light into different spatial directions; and a lighting control device configured for individually controlling the operation of the plurality of lighting modules for generating a desired light distribution of the light emitted by the plurality of lighting modules.

Abstract: A navigation light system for an unmanned aerial vehicle, such as a multicopter type unmanned aerial vehicle, includes: a plurality of light emission units. E of the plurality of light emission units has a unit-specific light emission direction and is configured to provide a light output around the unit-specific light emission direction. Each of the plurality of light emission units includes a multi-color light source capable of emitting red light, green light, and white light. The plurality of light emission units are arranged to jointly provide a navigation light pattern around the unmanned aerial vehicle and wherein the light outputs of adjacent light emission units have an overlap the navigation light system is configured to operate each of the plurality of light emission units depending on a relation between a momentary flight direction of the unmanned aerial vehicle and the respective unit-specific light emission direction.

Abstract: The present invention relates to a light guiding assembly, a vehicle lamp and a vehicle. Specifically, the light guide assembly includes at least a first light guide element and a second light guide element, which can be joined to form a predetermined shape, in the region where the first light guide element and the second light guide element are joined, the parts of the first light guide element and the second light guide element that face each other at least partially overlap, so that light leaving one of the first light guide element and the second light guide element can at least partially enter the other. The vehicle lamp and the vehicle have the abovementioned light guide assembly.

Abstract: A set of exterior aircraft lights, comprises a main landing light, which comprises at least one main landing light source and is configured for emitting a main landing light beam around a main landing light beam direction (L), and at least one of a taxi light and a runway turn-off light. The taxi light is configured for emitting a taxi light beam around a taxi light beam direction (T) and for emitting a first auxiliary landing light beam around a first auxiliary landing light beam direction (AL1), wherein the first auxiliary landing light beam direction (AL1), when projected onto a vertical plane, is angled downwards between 5° and 15° with respect to the straight ahead direction. The runway turn-off light is configured for emitting a runway turn-off light beam around a runway turn-off light beam direction (Ra, Rb).

Abstract: An illuminated aircraft passenger cabin gasper comprises an air outlet for outputting a flow of air into an aircraft passenger cabin and an air guide, movably arranged within the air outlet for adjusting the flow of air that includes a light guide. The gasper also includes at least one light source, arranged adjacent to the light guide for coupling light into the light guide. The light guide has a light output surface for coupling light out of the light guide into the aircraft passenger cabin.

Abstract: An aircraft navigation light includes: a navigation lighting arrangement, having: a power input, couple able to an aircraft on-board power supply network, at least one navigation light source, and a power conditioning circuit, coupled between the power input and the at least one navigation light source for conditioning a power flow from the power input to the at least one navigation light source; an auxiliary power supply, coupled to the power conditioning circuit for diverting power from the navigation lighting arrangement; and a power supply output, coupled to the auxiliary power supply, for supplying power from the auxiliary power supply to an exterior aircraft light, external to the aircraft navigation light.

Abstract: An exterior aircraft light includes a housing having a length (L), a width (W), and a height (H), the length (L) being greater than the width (W) and the height (H) and the housing having a front end region and a rear end region, wherein the housing is configured to be mounted on a tail portion of a fuselage of an aircraft; at least one first light source, arranged in the rear end region of the housing, for providing aircraft rearward signal lighting; and a plurality of second light sources, which are arranged spaced along the length (L) of the housing for a distributed illumination of a stabilizer of the aircraft.