A seatbelt detection system detects seatbelt use in each seat of a passenger aircraft to produce safety-compliance data. A computer system, which is communicatively coupled to the seatbelt detection system, receives sensor data from a plurality of sensors in an aircraft cabin; and employ an artificial intelligence (AI) program to train on input data comprising at least one of safety compliance data, aircraft system data, cabin environment data, cabin operations data, or aircraft operations data; and the AI program is configured to minimize a summed error of predictions of seatbelt compliance.

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.

An air cycle machine includes a compressor in fluid communication with a load cooling heat exchanger, a first valve and a first turbine connecting the compressor to the load cooling heat exchanger, and a second valve and a second turbine. The second valve and the second turbine connect the compressor to the load cooling heat exchanger and connected in parallel with the first valve and the first turbine between the compressor and the load cooling heat exchanger. Air cycle machine systems and methods of controlling air flow through air cycle machines are also described.

A bleed air supply system has a sensor monitoring the system, an operating condition monitor detecting an operating condition value of the aircraft (other than the bleed air supply system), and independent monitoring modules evaluating a part of the bleed air supply system. The monitoring modules each have an individual monitoring function and individual activation and deactivation parameters based on sensor data and the operating condition value. The method includes: detecting the condition of the bleed air supply system via sensor data and the operating condition value; activating a monitoring module, which has activation parameters met by the sensor data and the operating condition value; monitoring the condition of the bleed air supply system by the activated monitoring module by a monitoring function of the activated monitoring module; and deactivating the activated monitoring module, deactivation parameters of which are met by the sensor data and the operating condition value.

A duct is provided and includes a tubular member having an inlet portion, an outlet portion and a central portion interposed between the inlet and outlet portions and a tributary tubular member fluidly coupled to the tubular member at the central portion. The tributary tubular member includes first and second torus sectors defining first and second apertures, respectively, through which an upstream end of the central portion extends. The second torus sector is disposed within the first torus sector to define a sectioned toroidal annulus about the first and second apertures and between an exterior surface of the second torus sector and an interior surface of the first torus sector.

A method of operating an environmental control system of an aircraft includes providing a first medium to the environmental control system including a compressor and a turbine. The first medium is provided to the compressor and the turbine sequentially. A second medium is provided to the environmental control system. In a first mode of operation, the first medium and the second medium mix within the turbine and in a second mode of operation the second medium bypasses the turbine such that the first medium and the second medium mix downstream from the turbine.

An environmental control system for an aircraft includes a higher pressure tap associated with a higher compression location in a main compressor section. The higher pressure tap leads into a turbine section of a turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive a compressor section of the turbocompressor. A combined outlet receives airflow from a turbine outlet and a compressor outlet intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft system. A buffer air outlet communicates airflow to an engine buffer air system.

An air duct system is disclosed, and includes an air duct having a main body, where the main body of the air duct defines a passageway having a reflective inner surface. The air duct system also includes an ultraviolet light source configured to generate ultraviolet light. The ultraviolet light source directs the ultraviolet light along the reflective inner surface of the air duct.

An airfoil body for an aircraft extending from an inner end to an outer end, and between a leading edge and a trailing edge. The airfoil body comprises an internal structure and an airfoil skin covering the internal structure. The skin has a pressure side and a suction side, and the suction side includes a light transmitting portion. The internal structure includes an array of transduce elements attached to a planar sheet with the airfoil body. The present disclosure further relates to wings and aerial vehicles.

An environmental control system includes a compression device including a compressor, a turbine, and an electric motor operably coupled by a shaft. The electric motor and the turbine are arranged in series relative to a flow of a first medium.