Abstract: A sanitization system for an aircraft may comprise: a lighting system disposed in the aircraft cabin, the lighting system including a plurality of sanitization lights, the plurality of sanitization lights configured to emit UV-C radiation; an electrical port in electrical communication with the lighting system; an external power source disposed away from the aircraft; and an electrical cable coupled to the external power source, the electrical cable configured to removably couple to the electrical port to provide electrical power to the plurality of sanitization lights.

Abstract: A de-icing light assembly may comprise: a housing; a plurality of lights coupled to the housing; a lens assembly coupled to the housing, the lens assembly comprising: a lens material; an indium tin oxide (ITO) film disposed on the lens material; and a silicon oxide coating disposed on the ITO film.

Abstract: A system for controlling in-flight services using gestures is disclosed. The system comprises: a gesture detection device; an actuator; and a controller. The controller is configured to: receive a detected free space gesture from the gesture detection device; compare the detected free space gesture to a plurality of identified free space gestures; responsive to identifying a free space gesture from the plurality of identified free space gestures, identify an associated in-flight service based on the identified free space gesture; and responsive to identifying the associated in-flight service, send a first command to the actuator to perform the associated in-flight service.

Abstract: A lighting system and assembly comprising a controller in operable communication with a light unit. The controller is configured to apply a lighting condition using the light unit for a target light color below an upper level of NVIS radiance while controlling a Melanopic-Photopic (M/P) ratio associated with the target light color, and also determine a color mixing for producing NVIS Green A light and NVIS white light for a plurality of levels of NVIS radiance which are less than a maximum NVIS radiance level for a set of M/P ratio values at an upper allowable limit and a set of M/P ratio values at a lower limit.

Abstract: A fluid removal assembly for an aircraft light is provided. The fluid removal assembly includes a condensate removal valve including a housing; a set of helical compression springs; and a stem disposed within the housing. The stem is configured to translate in a first direction responsive to the aircraft being pressurized and a first force, from the pressurization, forcing the stem to translate in the first direction; and translate in a second direction opposite the first direction responsive to the aircraft being depressurized and a second force from the set of helical compression springs forcing the stem to translate in the second direction. The condensate removal valve is configured to: responsive to an aircraft being depressurized, drain a fluid from one or more components of the aircraft light, the aircraft light being installed in the aircraft; and responsive to the aircraft being pressurized, maintain a pressure within the aircraft.

Abstract: A light assembly includes a mounting bracket, a light coupled to the mounting bracket, a guide sensor coupled to the mounting bracket, a movement mechanism coupled to the mounting bracket, and a controller operably coupled to the light assembly. The controller is configured to receive data from the guide sensor and command actuation of the movement mechanism in response to the data received from the guide sensor.

Abstract: A system for controlling in-flight services using gestures is disclosed. The system comprises: a gesture detection device; an actuator; and a controller. The controller is configured to: receive a detected free space gesture from the gesture detection device; compare the detected free space gesture to a plurality of identified free space gestures; responsive to identifying a free space gesture from the plurality of identified free space gestures, identify an associated in-flight service based on the identified free space gesture; and responsive to identifying the associated in-flight service, send a first command to the actuator to perform the associated in-flight service.

Abstract: A system for displaying an artificial horizon in an enclosed space. The system includes a first plurality of visual effect sources located in the enclosed space and configured to generate a first visual effect of the artificial horizon consistent with an orientation detected by an orientation sensor. The system further includes a second plurality of visual effect sources separate from the first plurality of visual effect sources and located in the enclosed space and configured to generate a second visual effect of the artificial horizon different from the first visual effect consistent with the orientation detected by the orientation sensor.

Abstract: An aircraft light unit is disclosed herein. The aircraft light unit includes a housing having a first side and an opposing second side, a light coupled to the first side of the housing, a circuit board assembly coupled to second side of the housing, a thermoelectric cooler coupled to the circuit board assembly and configured to dissipated heat from the circuit board assembly, and a heat sink disposed over the thermoelectric cooler and configured to dissipate heat from the thermoelectric cooler.

Abstract: An autonomous light system may comprise a reading light assembly, an object detection device; and a controller. The reading light assembly may include a light source and an actuation system. The controller may be operably coupled to the light source and the object detection device. The controller may include an object detection module and may be configured to receive object data from the object detection device, compare the object data against an object database, identify an object based on the comparison of the object data to the object database, send a first command to at least one of the light source and the actuation system.

Abstract: A light assembly includes a mounting bracket, a light coupled to the mounting bracket, a guide sensor coupled to the mounting bracket, a movement mechanism coupled to the mounting bracket, and a controller operably coupled to the light assembly. The controller is configured to receive data from the guide sensor and command actuation of the movement mechanism in response to the data received from the guide sensor.

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: 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 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: 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: 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: 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: 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.