A fuel system is provided for an aircraft having a fuel source. The fuel system includes a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path is in airflow communication with the fuel source.

A fuel extraction system for extracting a gaseous fuel from a fuel tank. The fuel extraction system includes a conveying device which is configured to convey gaseous fuel and to bring it from a first pressure level to a second pressure level, a first line which is configured to connect the conveying device fluidically to the interior of the fuel tank, a buffer tank which is configured to store the fuel at the second pressure level, and which has a first outlet and a second outlet, at least one valve with a pneumatic actuating device, and a second line which is connected to the first outlet of the buffer tank and is configured to conduct a part of the fuel at the second pressure level to the pneumatic actuating device of the at least one valve. Furthermore, a fuel tank apparatus and a fuel cell system are described.

A fuel extraction system for extracting a gaseous fuel from a fuel tank. The fuel extraction system includes a conveying device which is configured to convey gaseous fuel and to bring it from a first pressure level to a second pressure level, a first line which is configured to connect the conveying device fluidically to the interior of the fuel tank, a buffer tank which is configured to store the fuel at the second pressure level, and which has a first outlet and a second outlet, at least one valve with a pneumatic actuating device, and a second line which is connected to the first outlet of the buffer tank and is configured to conduct a part of the fuel at the second pressure level to the pneumatic actuating device of the at least one valve. Furthermore, a fuel tank apparatus and a fuel cell system are described.

A fuel system is provided for an aircraft having a fuel source. The fuel system includes a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path is in airflow communication with the fuel source.

A fuel system is provided for an aircraft having a fuel source. The fuel system includes a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path is in airflow communication with the fuel source.

A duct stringer is disclosed and forms at least part of a duct with a closed cross-section along which a fluid flows. An aperture is formed through a duct wall of the duct stringer and communicates with the duct. An insert is adhered in the duct stringer and is configured to engage with a fastening member to mount a fluid transporting conduit, such as a pipe, over the aperture.

A fuel supply system for an aerial vehicle includes: a plurality of fixed tanks storing fuel; a variable tank provided in a fixed tank of the plurality of fixed tanks and storing fuel; a fuel supply flow path, a first end of which is connected to the variable tank and passing through the plurality of fixed tanks; and a fuel pump provided in a fixed tank which does not have the variable tank, an outlet side of the fuel pump being connected to the fuel supply flow path. According to the fuel supply system, continuous fuel supply is performed despite the change of the attitude or acceleration of an aerial vehicle, sufficient fuel is stored, and constraints on fuel tank design are minimized.

A fuel supply system for an aerial vehicle includes: a plurality of fixed tanks storing fuel; a variable tank provided in a fixed tank of the plurality of fixed tanks and storing fuel; a fuel supply flow path, a first end of which is connected to the variable tank and passing through the plurality of fixed tanks; and a fuel pump provided in a fixed tank which does not have the variable tank, an outlet side of the fuel pump being connected to the fuel supply flow path. According to the fuel supply system, continuous fuel supply is performed despite the change of the attitude or acceleration of an aerial vehicle, sufficient fuel is stored, and constraints on fuel tank design are minimized.

A fuel storage system is disclosed having a fuel tank configured to store a liquid fuel; a controllable pressure source for altering the pressure in an ullage space of the fuel tank; and a controller. The controller is configured to determine a target pressure for the ullage space at a given time based on information relating to a temperature of fuel inside the fuel tank at the given time; and to control the pressure source such as to cause the pressure in the ullage space to be substantially equal to the target pressure.

A fuel storage system is disclosed having a fuel tank configured to store a liquid fuel; a controllable pressure source for altering the pressure in an ullage space of the fuel tank; and a controller. The controller is configured to determine a target pressure for the ullage space at a given time based on information relating to a temperature of fuel inside the fuel tank at the given time; and to control the pressure source such as to cause the pressure in the ullage space to be substantially equal to the target pressure.