An airplane is provided. The airplane includes a fuel gauging and quantity estimation system with an improved estimation accuracy. The fuel gauging and quantity estimation system operates by detecting an environment of a tank comprising a liquid and selecting one or more liquid gauging algorithms based on the environment. The fuel gauging and quantity estimation system further operates by receiving sensor data characterizing the liquid of the tank and utilizing the sensor data and the one or more liquid gauging algorithms to determine a property of the liquid.

Fuel systems, apparatus and associated methods for preventing or hindering unwanted fuel transfer between fuel tanks of aircraft are described. An exemplary apparatus comprises a conduit portion disposed inside a fuel tank for receiving fuel in the first fuel tank. The conduit portion includes an orifice through a wall of the conduit. The orifice permits venting an interior of the conduit portion to an interior of the fuel tank to prevent unwanted fuel transfer due to siphoning. A deflector is disposed and configured to deflect a stream of fuel discharged from the orifice during fuel transfer.

Fuel systems, apparatus and associated methods for preventing or hindering unwanted fuel transfer between fuel tanks of aircraft are described. An exemplary apparatus comprises a conduit portion disposed inside a fuel tank for receiving fuel in the first fuel tank. The conduit portion includes an orifice through a wall of the conduit. The orifice permits venting an interior of the conduit portion to an interior of the fuel tank to prevent unwanted fuel transfer due to siphoning. A deflector is disposed and configured to deflect a stream of fuel discharged from the orifice during fuel transfer.

An energy production assembly includes a pump and at least one system for purging water contained in a fuel reservoir. The purging system (22) comprises a transport pipe and a sampling pipe, secured to the transport pipe, extending between a sampling inlet and a sampling outlet, the sampling inlet emerging in a region (36) of the reservoir (16) configured to accumulate water, the sampling outlet emerging in the transport pipe, upstream from or in the Venturi. The pump (14) is arranged downstream from the Venturi, and at least one region of the sampling pipe comprising the sampling outlet is coaxial with the transport pipe.

An aircraft comprises several elements. A throttle body is adapted to regulate a rate of air flow. An electronic control unit, in turn, is in signal communication with one or more sensors, and comprises a data processor in signal communication with a memory. A first fuel delivery system is operative to direct a first fuel from a first fuel tank to the plurality of cylinders at a rate determined at least in part by a condition of the throttle body. A second fuel delivery system is operative to direct a second fuel from a second fuel tank to the plurality of cylinders at a rate determined at least in part by the electronic control unit in response to signals from the one or more sensors. One or more fuel selection controls allow a pilot of the aircraft to select between powering the aircraft with the first fuel delivery system and the second fuel delivery system.

An aircraft comprises several elements. A throttle body is adapted to regulate a rate of air flow. An electronic control unit, in turn, is in signal communication with one or more sensors, and comprises a data processor in signal communication with a memory. A first fuel delivery system is operative to direct a first fuel from a first fuel tank to the plurality of cylinders at a rate determined at least in part by a condition of the throttle body. A second fuel delivery system is operative to direct a second fuel from a second fuel tank to the plurality of cylinders at a rate determined at least in part by the electronic control unit in response to signals from the one or more sensors. One or more fuel selection controls allow a pilot of the aircraft to select between powering the aircraft with the first fuel delivery system and the second fuel delivery system.

An apparatus contains a dihydrogen tank and/or a dihydrogen circuit, and a device for regulating a concentration of dihydrogen located outside the tank and/or the circuit. The device includes at least one pair of electrical conductors including a first electrical conductor supplied with a first voltage and a second electrical conductor supplied with a second voltage which is different from the first voltage. At least one controller repeatedly commands the application of a predetermined voltage difference between the first electrical conductor and the second electrical conductor so that an electric arc of controlled power is formed in order to burn dihydrogen possibly coming from the tank and/or from the circuit. Thus, dihydrogen does not accumulate in undesired places in the apparatus.

An apparatus contains a dihydrogen tank and/or a dihydrogen circuit, and a device for regulating a concentration of dihydrogen located outside the tank and/or the circuit. The device includes at least one pair of electrical conductors including a first electrical conductor supplied with a first voltage and a second electrical conductor supplied with a second voltage which is different from the first voltage. At least one controller repeatedly commands the application of a predetermined voltage difference between the first electrical conductor and the second electrical conductor so that an electric arc of controlled power is formed in order to burn dihydrogen possibly coming from the tank and/or from the circuit. Thus, dihydrogen does not accumulate in undesired places in the apparatus.

A method of determining an operating condition of a valve of an aircraft system includes obtaining a first time period associated with actuating the valve, and a second time period associated with actuating the valve. The method includes providing an indication of an altered operating condition associated with actuation of the valve based on the first and second time periods.

A fuel circuit of an aircraft engine including a fuel tank; an engine fuel system including a low-pressure pump and a high-pressure pump, and a fuel recirculating pipeline connected to the engine fuel system; and a fuel recirculating valve arranged so as to switch between an open position and a closed position according to the pressure differential of the low-pressure pump, the valve being able to obstruct the fuel recirculating pipeline in the closed position, and to bring the fuel recirculating pipeline into communication with the fuel tank in the open position.