Abstract: An aircraft emergency exit door indication system may comprise a first plurality of light sources, a controller, and a first sensor associated with a first exit door. The first sensor feedback signal indicates an availability for egress through the first exit door. The first plurality of light sources is operated by the controller based upon the first sensor feedback signal. The light sources may be lights that already exist in an aircraft such as ceiling wash lights, sidewall wash lights, floor path lights, dome lights, or passenger service unit lights. The system may include a second plurality of light sources logically separated from the first plurality of light sources based upon its location relative to the first exit door and a second exit door.

Abstract: Systems and methods for light emitting diodes (LEDs) circuits are provided. Aspects include a set of light emitting diodes (LEDs) arranged in series between a first node and a second node, a power supply coupled to the first node, a first switching element arranged in series between the first node and a third node, wherein the first switching element is in parallel with the set of LEDs, a first charge pump coupled to the third node, a controller configured to operate the first switching element by providing a control voltage for switching the first switching element between an ON and an OFF, wherein the control voltage comprises a switching frequency, and wherein the first charge pump is charged by the power supply responsive to the switching element being in an ON state.

Abstract: A cast concrete durable light fixture design and assembly that will allow in-ground lighting features for roadways, pathways and architectural features providing a simple installation for a drive over in-grade or in-ground lighting fixture. The cast concrete design enables curves and shapes to be manufactured as easily as straight or linear configurations.

Abstract: Systems and methods for operating light emitting diodes (LEDs) circuits are provided. Aspects include a power supply coupled to the first node, a set of light emitting diodes (LEDs) arranged in series between a second node and a third node, a boost converter coupled to the first node and the second node, a first control circuit configured to operate a first switching element to control operation of the boost convertor, wherein the boost convertor outputs a step-up voltage to drive the set of LEDs, and a second control circuit to operate the second switching element to control operation of the set of LEDs, the second switching element coupled to the third node, wherein the set of LEDs are ON responsive to the second switching element being in an ON state.

Abstract: A modular light assembly having a control housing surrounding a power driver and at least one modular component. The modular component includes two side portions, a plurality of ribs extending between the two side portions to form a grated portion, and a flat portion configured to receive a COB LED. The lighting assembly may also comprise a video assembly having a camera and control circuitry provided within the lighting and video assembly for remotely controlling the camera.

Abstract: The present disclosure provides a night vision imaging system (NVIS) lighting system, comprising a frame comprising a first light source, a second light source adjacent to the first light source, a third light source adjacent to the second light source, and a diffuser mounted to the frame and encasing the first light source, the second light source, and the third light source. The first light source may comprise a first dominant wavelength, the second light source may comprise a second dominant wavelength different from the first dominant wavelength, and the third light source may comprise a third dominant wavelength different from the first dominant wavelength and the second dominant wavelength. Light emitted from the first light source, the second light source, and the third light source may be blended to generate a first blended light source comprising a first target output color.

Abstract: A light assembly for use on an aircraft is disclosed herein. The light assembly comprises a reflector assembly, a printed wiring assembly, and a bezel assembly. The bezel assembly may comprise a first worm screw. The first worm screw may be configured to translate at least one of the reflector assembly and the printed wiring assembly in a first direction. The bezel assembly may comprise a second worm screw. The second worm screw may be configured to translate at least one of the reflector assembly and the printed wiring assembly in a second direction.

Abstract: A disconnect component coupled between a lighting load and a main power line. The disconnect component includes an input coupled to the main power line and a neutral line input to the disconnect component from the 277 volt circuit and an output coupled to the lighting load. The disconnect component includes a monitor that monitors a voltage on the main power line and a coupling component that couples the main power line to the output. The coupling component is configured to decouple the main power line from the output when the monitor senses a voltage on the main power line is higher than an upper limit voltage and re-couple the main power line to the output when the monitor senses that the voltage on the main power line is below the upper limit voltage.

Abstract: A disconnect component coupled between a lighting load and a main power line. The disconnect component includes an input coupled to the main power line and a neutral line input to the disconnect component from the 277 volt circuit and an output coupled to the lighting load. The disconnect component includes a monitor that monitors a voltage on the main power line and a coupling component that couples the main power line to the output. The coupling component is configured to decouple the main power line from the output when the monitor senses a voltage on the main power line is higher than an upper limit voltage and re-couple the main power line to the output when the monitor senses that the voltage on the main power line is below the upper limit voltage.

Abstract: An aircraft emergency exit door indication system may comprise a first plurality of light sources, a controller, and a first sensor associated with a first exit door. The first sensor feedback signal indicates an availability for egress through the first exit door. The first plurality of light sources is operated by the controller based upon the first sensor feedback signal. The light sources may be lights that already exist in an aircraft such as ceiling wash lights, sidewall wash lights, floor path lights, dome lights, or passenger service unit lights. The system may include a second plurality of light sources logically separated from the first plurality of light sources based upon its location relative to the first exit door and a second exit door.

Abstract: A modular light assembly having a control housing surrounding a power driver and at least one modular component. The modular component includes two side portions, a plurality of ribs extending between the two side portions to form a grated portion, and a flat portion configured to receive a COB LED. The lighting assembly may also comprise a video assembly having a camera and control circuitry provided within the lighting and video assembly for remotely controlling the camera.

Abstract: A dual mode light includes a housing, at least one first light emitter disposed in the housing, a plurality of second light emitters each disposed in the housing an emitter distance from the at least one first light emitter, a first shield disposed in the housing a first shield distance from the at least one first light emitter, wherein the first shield distance is less than the emitter distance, and a second shield disposed in the housing a second shield distance around the plurality of second light emitters.

Abstract: An LED light system for an aircraft may comprise a first LED lamp having a first LED array. The first LED array may include at least a first LED and a second LED. A first optical element may be configured to direct light emitted from the first LED in a first beam centered around a first angle and to direct light emitted from the second LED in a second beam centered around a second angle. The LED light system may further comprise a second LED lamp having a second LED array. The second LED array may include at least a third LED and a fourth LED. A second optical element may be configured to direct light emitted from the third LED in a third beam centered around the first angle and to direct light emitted from the fourth LED in a fourth beam centered around the second angle.

Abstract: An LED light system for an aircraft may comprise a first LED lamp having a first LED array. The first LED array may include at least a first LED and a second LED. A first optical element may be configured to direct light emitted from the first LED in a first beam centered around a first angle and to direct light emitted from the second LED in a second beam centered around a second angle. The LED light system may further comprise a second LED lamp having a second LED array. The second LED array may include at least a third LED and a fourth LED. A second optical element may be configured to direct light emitted from the third LED in a third beam centered around the first angle and to direct light emitted from the fourth LED in a fourth beam centered around the second angle.

Abstract: An LED light system for an aircraft may comprise a first LED lamp having a first LED array. The first LED array may include at least a first LED and a second LED. A first optical element may be configured to direct light emitted from the first LED in a first beam centered around a first angle and to direct light emitted from the second LED in a second beam centered around a second angle. The LED light system may further comprise a second LED lamp having a second LED array. The second LED array may include at least a third LED and a fourth LED. A second optical element may be configured to direct light emitted from the third LED in a third beam centered around the first angle and to direct light emitted from the fourth LED in a fourth beam centered around the second angle.

Abstract: A dual mode light assembly for a forward position light of an aircraft includes a base, a visible light source mounted to the base that is configured to emit visible light, a covert light source mounted to the base that is configured to emit covert light, and a light shield mounted to the base. The light shield is configured to restrict transmission of the visible light to a visible light pattern and to restrict transmission of the covert light to a covert light pattern.

Abstract: A dual mode light assembly for a forward position light of an aircraft includes a base, a visible light source mounted to the base that is configured to emit visible light, a covert light source mounted to the base that is configured to emit covert light, and a light shield mounted to the base. The light shield is configured to restrict transmission of the visible light to a visible light pattern and to restrict transmission of the covert light to a covert light pattern.

Abstract: A light source includes a circular light element having a light source diameter, and a reflector disposed at least partially within the circular light element, the reflector having a first end with a first diameter and a second end with a second diameter, wherein the first diameter is less than the light source diameter and the second diameter is larger than the light source diameter, the second end having a plurality of slits.

Abstract: A device for projecting an image on a projector module screen, comprising an interchangeable disc including at least one image disposed thereon and a light source for illuminating the at least one image. The device further includes a lens for receiving the at least one image from the interchangeable disc and passing the image to the projector module screen, wherein the projector module screen displays the image and a projector module housing enclosing the interchangeable disc, the light source, and the lens.

Abstract: A system and method for estimating a distance between an aircraft and an object is disclosed. An exterior light of the aircraft transmit a test light signal and a parameter the transmitted test light signal is measured. A sensor receives a reflection of the test light signal from the object and the parameter is measured for the reflection test signal. The distance between the aircraft and the object is estimated using the parameter of the reflection and the parameter of the test light signal. The exterior light is generally a light that is built into the aircraft during aircraft construction while the sensor is retrofitted onto the aircraft.