Device for fitting two connectors at the end of two conduits, particularly in an aircraft, with a view to subsequent mutual connection of the connectors by a connecting pipe, including a body; a first support including temporary connector retainers that define an associated connector axis; an opposite second support including temporary connector retainers that define an associated connector axis; structure for moving the first support in translation relative to the body parallel to the associated connector axis, between a retracted position and a deployed position. A method of establishing fluidic communication between two conduits in an aircraft, including fitting two connectors at the end of the two conduits by such a device.

Device for fitting two connectors at the end of two conduits, particularly in an aircraft, with a view to subsequent mutual connection of the connectors by a connecting pipe, including a body; a first support including temporary connector retainers that define an associated connector axis; an opposite second support including temporary connector retainers that define an associated connector axis; structure for moving the first support in translation relative to the body parallel to the associated connector axis, between a retracted position and a deployed position. A method of establishing fluidic communication between two conduits in an aircraft, including fitting two connectors at the end of the two conduits by such a device.

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.

A method can include emitting, from a light source, directional light through fuel contained in a fuel tank, and determining a refraction angle of the directional light after the directional light passes through an interface with the fuel. The method can further include determining, by a processing device, an index of refraction of the fuel based on the determined refraction angle, and determining, by the processing device, a density of the fuel based on the determined index of refraction of the fuel.

A method can include illuminating an interior of a fuel tank with one or more light pulses, and receiving reflected returns of the one or more light pulses at a light sensor array. The method can further include producing, by a processing device, three-dimensional image data of the interior of the fuel tank based on the received reflected returns, producing, by the processing device, a fuel measurement value representing an amount of fuel contained in the fuel tank based on the three-dimensional image data, and outputting, by the processing device, an indication of the fuel measurement value.

A method can include generating reference image data representing a field of view of an interior of a fuel tank, and generating active image data representing the field of view of the interior of the fuel tank when the fuel tank contains fuel. The method can further include producing, by a processing device, a fuel measurement value representing an amount of fuel contained in the fuel tank based on the reference image data and the active image data, and outputting, by the processing device, an indication of the fuel measurement value.

A method can include generating reference image data representing a field of view of an interior of a fuel tank, and generating active image data representing the field of view of the interior of the fuel tank when the fuel tank contains fuel. The method can further include producing, by a processing device, a fuel measurement value representing an amount of fuel contained in the fuel tank based on the reference image data and the active image data, and outputting, by the processing device, an indication of the fuel measurement value.