A vessel designed for enclosing at least one sensor is arranged within a fuel tank. The vessel is provided with a fuel inlet connected to a refuelling arrangement of the tank, and with through-holes for the fuel to exit the vessel to the tank or to enter the vessel from the tank. It allows that measurement results which are provided by the sensor during a refuelling operation relate to the fuel currently admitted into the tank, separately from the fuel initially contained in the tank before the refuelling operation has started.

A method for manufacturing a strainer, such as a strainer of an ejector used to transfer fuel between two tanks of an aircraft or to supply fuel to an engine is provided. The strainer includes a conduit whereof a first end is intended to be connected to an inlet of the ejector, and whereof a second end is located within a housing including an open face for the passage of fuel, the open face being closed off by a grate acting as a filter. The method includes the step of manufacturing the conduit, the housing and the grate of the strainer as a single monobloc part.

Embodiments of the present invention provide a lever quick connect and disconnect fitting that provides a secure fit for tank-to-tank connections and prevents any leakage from occurring. The fitting provide two separate, independent locking features that can secure tank sleeves to one another. There is provided male and female components that are coupled together by a lever connect and by a safety ring.

A fuel cell power pack used as a power source in a multicopter includes a fuel tank and a fuel cell stack for producing electrical energy using hydrogen supplied from the fuel tank and supplying the electrical energy to a battery, and since the fuel cell stack is disposed at a certain point of an arm extended from the aircraft body in the radius direction (a point affected by a descending air current generated by each rotating blade), the electrical energy can be produced using the descending air current generated by the rotating blade without configuring a separate blowing apparatus.

A zero fuel time is determined and presented to an operator of an unmanned aerial vehicle (UAV). Zero fuel time may be determined based on a fuel burn rate and an amount of remaining fuel. A return to base time is determined and presented to an operator of a UAV. Return to base time may be determined based on a location of the UAV and a location of a base. Zero fuel time and return to base time are presented to an operator of a UAV proximate to one another using contrasting and/or varying visual characteristics to ease comparison and identification of this data.

The invention relates to a method for metering fuel in a fuel supply circuit of an aircraft engine, the circuit comprising a metering device for a fuel circuit of an aircraft engine comprising, downstream of a fuel pumping system and upstream of injectors: —a fuel inlet (E), —a metering device (FMV) and a cut-off device (HPSOV) arranged in series, —an adjustment valve (VR) arranged on a fuel recirculation branch, such that any excess fuel supplied by the pumping system is fed back into the fuel circuit, wherein at least one flow-metric sensor (WFM1) is arranged on the recirculation branch, a density value for the metered fuel is determined according to the sensor measurements and the metering device is controlled according to the fuel density value thus determined.

A pipe element suitable for use in a fuel system of an aircraft comprises an inner pipe and an outer pipe sealingly surrounding the inner pipe and connected to the inner pipe. The pipe element is constructed in one piece and is produced by a 3D printing process.

A bonding wire conductively connected to a pipe having a pipe body and a conductive tab mounted to the pipe and having a hole therein, the bonding wire being in the form of a braided conductive cable provided with a connector at each of its ends, the bonding wire being tightly wound around the pipe body and the ends both passing through the hole in the connector such that the ends of the bonding wire extend away from the pipe body after passing through the hole, while a portion of the bonding wire between the end portions is wrapped tightly around the pipe body; the bonding wire held under tension around the pipe body by a crimp around the two end portions where they pass through the hole.

A tank defines an inner cavity and at least an opening. A filler tube device comprises a tube passing through the opening in the tank, the tube forming a joint with at least one degree of freedom with the tank such that the tube is displaceable relative to the tank. The tube has an open end in the inner cavity of the tank, and an opposite open end outside of the tank, whereby the tube defines a passage for filling the tank. A sealing component is in the inner cavity of the tank, the sealing component configured for collaborating with the open end of the tube when the tube is moved into engagement therewith to close the open end of the tube inside the tank in a protective position.

A method for the circulation of fuel in an aircraft uses at least one diaphragm pump having an undulating diaphragm that can undulate between two flanges, under the action of an actuator, for circulating the fuel between an admission line of the pump and an exhaust line of the pump.