A tank system for an aircraft, including a tank including an inner enclosure including a closed inner skin configured to store dihydrogen and an outer enclosure including an outer skin that surrounds the inner enclosure, a chassis including a front frame at a front end of the tank, and an attachment arrangement which attaches the outer skin of the outer enclosure to the front frame. A system of this kind makes it possible to react forces through the outer skin, thus reducing a complexity of the chassis.

A tank system for an aircraft, including a tank including an inner enclosure including a closed inner skin configured to store dihydrogen and an outer enclosure including an outer skin that surrounds the inner enclosure, a chassis including a front frame at a front end of the tank, and an attachment arrangement which attaches the outer skin of the outer enclosure to the front frame. A system of this kind makes it possible to react forces through the outer skin, thus reducing a complexity of the chassis.

An inerting system includes a fluid circuit, a reactor within the fluid circuit, at least one particulate removal device (PRD) downstream from the reactor, and a fluid tank. The fluid tank is downstream from the at least one PRD. A method for removing particulates from a fluid stream in a fluid circuit includes receiving a fluid stream in a reactor within a fluid circuit, outputting an exhaust stream from the reactor, receiving the exhaust stream in at least one PRD downstream from the reactor, removing particulate from the exhaust stream, and receiving the exhaust stream with particulate removed in a fluid tank downstream from the at least one PRD.

Renewable fuel power systems for vehicles, such as aircraft, are provided. For example, a system includes a storage tank, a reactor module, a heat exchanger unit, and a combustion engine. The storage tank is configured to store ammonia in liquid form. The reactor module is in fluid communication with the storage tank. The reactor module is configured to extract hydrogen from the ammonia, and output fuel which includes the extracted hydrogen. The heat exchanger unit is configured to heat the ammonia which flows from the storage tank to an input of the reactor module, using heat which is extracted from the fuel that is output from the reactor module. The combustion engine is configured to combust the fuel provided by the reactor module, to thereby produce mechanical power.

An aircraft wing box is disclosed having a fuel tank with a fuel-tight boundary, upper and lower covers, forward and aft spars, and a partition including an inboard portion, an outboard portion, and a third portion between the inboard and outboard portions. Each cover is attached to each spar, the inboard portion of the partition is joined to each cover and joined to one of the spars, the outboard portion of the partition is joined to each cover and joined to one of the spars, each cover is joined to the partition. The inboard part, outboard part and third part of the partition are integrally formed as a single-piece; and the single-piece provides part of the fuel-tight boundary of the fuel tank.

An aircraft wing box is disclosed having a fuel tank with a fuel-tight boundary, upper and lower covers, forward and aft spars, and a partition including an inboard portion, an outboard portion, and a third portion between the inboard and outboard portions. Each cover is attached to each spar, the inboard portion of the partition is joined to each cover and joined to one of the spars, the outboard portion of the partition is joined to each cover and joined to one of the spars, each cover is joined to the partition. The inboard part, outboard part and third part of the partition are integrally formed as a single-piece; and the single-piece provides part of the fuel-tight boundary of the fuel tank.

A system and method of controlling a fuel system on an aircraft includes selectively supplying fuel from either a main fuel tank or at least one wing fuel tank to a fuel consumer by varying a speed of at least one main fuel tank pump associated with the main fuel tank relative to a speed of at least one wing fuel tank pump associated with the at least one wing fuel tank.

A system and method of controlling a fuel system on an aircraft includes selectively supplying fuel from either a main fuel tank or at least one wing fuel tank to a fuel consumer by varying a speed of at least one main fuel tank pump associated with the main fuel tank relative to a speed of at least one wing fuel tank pump associated with the at least one wing fuel tank.

Provided is a flight vehicle that makes it possible to improve the safety of its passengers. The flight vehicle, which includes a fuel cell system, includes a fuselage part including a cabin. The fuel cell system includes at least one fuel gas tank, and a lower end of the fuel gas tank stands below a lower end of the fuselage part.

Provided is a flight vehicle that makes it possible to improve the safety of its passengers. The flight vehicle, which includes a fuel cell system, includes a fuselage part including a cabin. The fuel cell system includes at least one fuel gas tank, and a lower end of the fuel gas tank stands below a lower end of the fuselage part.