Described herein are systems and methods for liquid phase separation for fuel tanks and other vessels. Particularly, aspects of the present disclosure are directed to a backpressure regulator configured to open when pressure of a mixture upstream of the backpressure regulator exceeds a predetermined setpoint and a hydrophobic membrane upstream of the backpressure regulator and downstream of a first conduit. The predetermined setpoint may be determined by at least a bubble point pressure of the hydrophobic membrane. Additionally, the backpressure regulator may be fluidically connected to and downstream of the first conduit, and to at least one pump operably connected to and upstream of the first conduit and the hydrophobic membrane may be fluidically connected to and upstream of a second conduit. The backpressure regulator may be fluidically connected to and upstream of a third conduit and the third conduit may be downstream the first conduit.

The present disclosure provides an apparatus (100) for recovering an unmanned vehicle (20), comprising: a container (103) for storing at least one unmanned vehicle (20), the container (103) having an opening (105) for receiving an unmanned vehicle (20) an extendable tether (102), a first end of the tether (102) being coupled to the inside of the container (103), a second end of the tether being arranged to pass through the opening (105); and at least one light source (106) affixed to the second end of the tether (102). The present disclosure also provides an aircraft (10) having the apparatus (100), an unmanned vehicle (20) to be recovered and methods of recovering an unmanned vehicle.

The present disclosure provides an apparatus (100) for recovering an unmanned vehicle (20), comprising: a container (103) for storing at least one unmanned vehicle (20), the container (103) having an opening (105) for receiving an unmanned vehicle (20) an extendable tether (102), a first end of the tether (102) being coupled to the inside of the container (103), a second end of the tether being arranged to pass through the opening (105); and at least one light source (106) affixed to the second end of the tether (102). The present disclosure also provides an aircraft (10) having the apparatus (100), an unmanned vehicle (20) to be recovered and methods of recovering an unmanned vehicle.

The present disclosure provides systems and methods for storing, transporting, and using hydrogen. In some embodiments, the method may comprise (a) storing hydrogen fuel in one or more fuel storage modules; (b) transporting the one or more fuel storage modules to a vehicle fueling site, wherein one or more hydrogen fuel compatible vehicles are located at or near the vehicle fueling site; (c) loading the one or more fuel storage modules into the one or more hydrogen fuel compatible vehicles, wherein the one or more fuel storage modules are configured to be releasably coupled to the one or more hydrogen fuel compatible vehicles; and (d) decoupling the one or more fuel storage modules from the one or more hydrogen fuel compatible vehicles after the one or more fuel storage modules are depleted or partially depleted.

The present disclosure provides systems and methods for storing, transporting, and using hydrogen. In some embodiments, the method may comprise (a) storing hydrogen fuel in one or more fuel storage modules; (b) transporting the one or more fuel storage modules to a vehicle fueling site, wherein one or more hydrogen fuel compatible vehicles are located at or near the vehicle fueling site; (c) loading the one or more fuel storage modules into the one or more hydrogen fuel compatible vehicles, wherein the one or more fuel storage modules are configured to be releasably coupled to the one or more hydrogen fuel compatible vehicles; and (d) decoupling the one or more fuel storage modules from the one or more hydrogen fuel compatible vehicles after the one or more fuel storage modules are depleted or partially depleted.

A device for refueling an aircraft, including a fuel flow duct, the downstream end of which is equipped with a wing coupler for connecting it to an inlet orifice of a fuel tank of the aircraft. The wing coupler includes a body, and a front valve that is movable with respect to the body. The wing coupler includes at least one detection member for detecting the position of the front valve, and an electrical or electronic transmission system for transmitting to a processing unit a signal representing the position of the front valve as detected by the at least one detection member.

A device for refueling an aircraft, including a fuel flow duct, the downstream end of which is equipped with a wing coupler for connecting it to an inlet orifice of a fuel tank of the aircraft. The wing coupler includes a body, and a front valve that is movable with respect to the body. The wing coupler includes at least one detection member for detecting the position of the front valve, and an electrical or electronic transmission system for transmitting to a processing unit a signal representing the position of the front valve as detected by the at least one detection member.

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.

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.

The present application discloses a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft, the gas turbine engine having a combustor supplied with fuel from a fuel system, the method comprising: determining a mass of the fuel being supplied to the combustor; determining a corresponding volume of the fuel being supplied to the combustor; and determining one or more fuel characteristics based on the determined mass and volume. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.