A method for calibrating a device for measuring a mass of fuel carried by an aircraft by: receiving a message containing a reference permittivity, a reference density and a reference volume, determining a first calibration coefficient as a function of the reference permittivity, determining a second calibration coefficient as a function of the reference volume, determining a third coefficient of calibration as a function of the reference density, determining a calibrated mass of fuel as a function of a determined height of fuel corrected as a function of the first calibration coefficient, a volume of fuel determined as a function of the corrected height and corrected as a function of the second calibration coefficient, and a mass of fuel determined as a function of the corrected volume and corrected as a function of the third calibration coefficient.

A coating system for applying coating liquid such as a base coat, a paint, a lacquer or a protective layer to surfaces of buildings, wind turbines, ships and aircraft. The coating system includes an unmanned aerial machine in the form of a helicopter for dispensing the coating liquid. The aerial machine has a fuselage, two rotors, a tank for holding the coating liquid, and an applicator for dispensing the coating liquid and outputting same onto a surface to be coated. In order to supply the tank with coating liquid, the tank is fastened to the aerial vehicle and the tank or aerial vehicle has a filling opening for refilling the tank in the landed state of the vehicle, and/or the tank is part of an exchangeable tank module coupled to the fuselage and/or is uncoupled from the fuselage by a coupling device controlled in an automated manner.

A coating system for applying coating liquid such as a base coat, a paint, a lacquer or a protective layer to surfaces of buildings, wind turbines, ships and aircraft. The coating system includes an unmanned aerial machine in the form of a helicopter for dispensing the coating liquid. The aerial machine has a fuselage, two rotors, a tank for holding the coating liquid, and an applicator for dispensing the coating liquid and outputting same onto a surface to be coated. In order to supply the tank with coating liquid, the tank is fastened to the aerial vehicle and the tank or aerial vehicle has a filling opening for refilling the tank in the landed state of the vehicle, and/or the tank is part of an exchangeable tank module coupled to the fuselage and/or is uncoupled from the fuselage by a coupling device controlled in an automated manner.

Aircraft hydrogen fuel systems and methods and systems of starting such systems are described. The aircraft hydrogen fuel systems include a hydrogen burning main engine, a main tank configured to contain liquid hydrogen to be supplied to the main engine during a normal operation, and a starter tank configured to contain gaseous hydrogen to be used during a startup operation of the main engine. Methods and processes for starting and/or restarting such systems are described.

A refueling system for hydrogen fuel cell-powered aircraft is disclosed. The system includes a compressor to receive a source of low temperature, high pressure hydrogen gas and compress the low temperature, high pressure hydrogen gas into a higher temperature, higher pressure hydrogen gas. A compression chamber within the compressor to receive the higher temperature, higher pressure hydrogen gas from the compressor. A valve coupled with the compression chamber to reduce the pressure of the higher temperature, higher pressure hydrogen gas to a higher temperature, lower pressure hydrogen gas. A storage container on an aircraft to receive the higher temperature, lower pressure hydrogen gas via the pressure relief valve. A heat exchanger in thermal cooperation with the compression chamber, the heat exchanger configured to absorb heat from the compression chamber and convert the heat into storable energy.

A heat exchanger comprises an inlet, an outlet, a heat exchanging channel, and an opening. The heat exchanging channel surrounds a cavity. The opening provides access to the cavity. The inlet is coupled to one end of the heat exchanging channel and the outlet is coupled to another end of the heat exchanging channel. The heat exchanging channel is isolated from the cavity. No access or passage is present between the heat exchanging channel and the cavity. During operation, heat exchanging fluid flows through the heat exchanging channel thereby cooling fluid within the cavity. The heat exchanging fluid never contacts the fluid within the cavity. In various embodiments, the heat exchanging channel has a single or stacked layer when viewed along a cross section. The heat exchanging channel has a spherical, cylindrical, or rectangular shape. In one embodiment, an insulative layer is disposed between layers of the heat exchanging channel.

An aircraft aerial refueling system including at least one pressure controlled fuel pump having a control system adapted to regulate the pump outlet fuel pressure using an outlet fuel pressure signal as control feedback. Also, methods of operating an aircraft aerial refueling system.

An aircraft aerial refueling system including at least one pressure controlled fuel pump having a control system adapted to regulate the pump outlet fuel pressure using an outlet fuel pressure signal as control feedback. Also, methods of operating an aircraft aerial refueling system.

A receiver surge test tool (STT) assembly, system and method for receiver surge pressure testing. The receiver STT assembly has a receiver surge test tool (STT) configured to simulate surge pressure conditions of a receiver aircraft, and to measure one or more surge pressures generated when receiving a fuel flow of fuel from a refueling source during the receiver surge pressure testing that is ground based. The receiver STT has a pipe manifold structure with inlet port(s), outlet port(s), and one or more flow lines disposed therebetween. Each flow line includes a flow meter, a pressure transducer, a shutoff valve having varying valve close rates, and a manual back pressure valve. The receiver STT assembly has a control system for controlling open and close positions of the shutoff valve, and the receiver STT, and has a data system for collecting and recording data generated during the receiver surge pressure testing.

A system ensures the correct type of fuel is dispensed in an aircraft while removing the introduction of human error in the refueling process. The system includes an RFID tag disposed at one or more aircraft that electronically stores data such as engine type, engine hours, fuel type, tail number, and pilot/subscriber data for the aircraft on which the RFID tag is disposed. An RFID reader is disposed at or near a fuel dispensing mechanism, such as a fuel truck or tank. A signal indicative of fuel type is emitted from the RFID tag to the RFID reader. RFID tags on aircraft that are enrolled in the system's subscription service enable aircraft to be recognized by a module operating the fuel dispensing mechanism. Based on a comparison performed by the module, authorization to begin fueling is either permitted or declined.