A lighting assembly for an aircraft includes a visible light source generating visible light and an ultraviolet light source generating ultraviolet light. The visible light source is disposed adjacent to the ultraviolet light source. The visible light source illuminates a first illumination area with the visible light when the lighting assembly operates in a first operation mode. The ultraviolet light source illuminates a second illumination area with the ultraviolet light when the lighting assembly operates in a second mode of operation. The first illumination area substantially overlaps the second illumination area.

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.

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.

Systems and methods for an aircraft lighting system (ALS) are provided. The method includes co-locating a central light source subsystem including a blue light generator, red light generator, and green light generator, and a light generating control unit (LGCU) comprising a processor, and distributing a plurality of passive light-heads around an external surface of the aircraft. Each passive light-head of the plurality of passive light-heads is operationally coupled to a first side of a respective light switch of a respective plurality of light switches, the light switch being coupled on a second side to a light emitting output of the central light source subsystem. Controlling and actuating the light generators and the light switches in accordance with a load profile is performed by a light generating control unit (LGCU).

A self-powered, wireless lighting system for an aircraft evacuation system. The lighting system includes a piezoelectric sensor configured to generate electrical energy under an aircraft evacuation event when the aircraft evacuation system is deployed, and a first light source disposed on the aircraft evacuation system, the first light source configured to provide illumination to the aircraft evacuation system. The piezoelectric sensor is operably connected to the first light source and configured to supply electrical energy to the light source based on vibrations in the evacuation system during deployment of the evacuation system and during use of the evacuation system as passengers evacuate the aircraft.

A self-powered, wireless lighting system for an aircraft evacuation system. The lighting system includes a piezoelectric sensor configured to generate electrical energy under an aircraft evacuation event when the aircraft evacuation system is deployed, and a first light source disposed on the aircraft evacuation system, the first light source configured to provide illumination to the aircraft evacuation system. The piezoelectric sensor is operably connected to the first light source and configured to supply electrical energy to the light source based on vibrations in the evacuation system during deployment of the evacuation system and during use of the evacuation system as passengers evacuate the aircraft.

An autonomous search light system for being mounted to an aircraft includes a search light for emitting an adjustable light output; an RF receiver with at least two RF antennas for receiving RF signals emitted by an RF transmitter; and a controller for determining a position of the RF transmitter in relation to the search light from the received RF signals and for controlling the search light based on the determined position of the RF transmitter.

A system for use in generating a power signal includes a first stage circuit having: a first input line coupled to a first stage first parallel line having a first stage first switch positioned thereon, a second input line coupled to a first stage second parallel line having a first stage second switch positioned thereon, and a first stage third parallel line oriented in parallel with the first stage first parallel line and the first stage second parallel line between a positive rail and a negative rail, the first stage third parallel line having a first capacitor positioned thereon. The system further includes a second stage circuit having a resonant inverter coupled between the positive rail and the negative rail and configured to output the power signal.

A system for use in generating a power signal includes a first stage circuit having: a first input line coupled to a first stage first parallel line having a first stage first switch positioned thereon, a second input line coupled to a first stage second parallel line having a first stage second switch positioned thereon, and a first stage third parallel line oriented in parallel with the first stage first parallel line and the first stage second parallel line between a positive rail and a negative rail, the first stage third parallel line having a first capacitor positioned thereon. The system further includes a second stage circuit having a resonant inverter coupled between the positive rail and the negative rail and configured to output the power signal.

A system for controlling a power signal for zero voltage switching (ZVS) includes a voltage zero crossing detection module to detect a zero voltage condition in response to an inverter voltage from a resonant inverter crossing zero volts, and a current zero crossing detection module to detect a zero current condition in response to an inverter current from the resonant inverter crossing zero amps. The system further includes a phase detect module to detect actual phase data corresponding to an actual phase angle between the inverter voltage and the inverter current based on the zero voltage and zero current condition. The system further includes a comparator to determine a phase difference between a desired phase between the inverter voltage and the inverter current and the actual phase angle. The system further includes a controller to adjust a property of a resonant inverter to reduce the phase difference.