Aircraft, comprising a carrier structure system and a device for carrying fuel, wherein the device comprises: a carrier element for the aircraft, wherein the carrier element has a longitudinal axis , at least three tanks , wherein a first tank is configured to contain hydrogen, a second tank is configured to contain water, and a third tank is configured to contain oxygen, wherein the at least three tanks are arranged successively along the carrier element , wherein the first, second and third tank are arranged such that a combined centre of gravity of the first tank and of the third tank is arranged on a centre of gravity of the second tank , the tanks having a side wall , an end wall and a chamber , which is at least partially delimited by the side wall and the end wall , for receiving the fuel; wherein the tanks are arranged in the carrier element and wherein the chamber and the side wall extend in a direction along the longitudinal axis ; wherein the side wall has a pressure-receiving component , wherein the pressure-receiving component is configured to convert a pressure from the chamber on the side wall and the end wall into a contraction force configured to act on the side wall along the longitudinal axis , wherein the contraction force is configured to compensate for an expansion force, resulting from the pressure from the chamber and acting on the side wall and the end wall along the longitudinal axis; wherein the pressure-receiving component is a fibre material which is wound around the longitudinal axis , wherein at least one portion of the fibre material assumes an angle relative to the longitudinal axis of between 40° and 50°, wherein the device is connected to the carrier structure system by means of the carrier element , and wherein the aircraft has a fuel cell which is connected to the at least three tanks via at least one line . a carrier element for the aircraft, wherein the carrier element has a longitudinal axis , at least three tanks , wherein a first tank is configured to contain hydrogen, a second tank is configured to contain water, and a third tank is configured to contain oxygen, wherein the at least three tanks are arranged successively along the carrier element , wherein the first, second and third tank are arranged such that a combined centre of gravity of the first tank and of the third tank is arranged on a centre of gravity of the second tank , the tanks having a side wall , an end wall and a chamber , which is at least partially delimited by the side wall and the end wall , for receiving the fuel; wherein the tanks are arranged in the carrier element and wherein the chamber and the side wall extend in a direction along the longitudinal axis ; wherein the side wall has a pressure-receiving component , wherein the pressure-receiving component is configured to convert a pressure from the chamber on the side wall and the end wall into a contraction force configured to act on the side wall along the longitudinal axis , wherein the contraction force is configured to compensate for an expansion force, resulting from the pressure from the chamber and acting on the side wall and the end wall along the longitudinal axis; wherein the pressure-receiving component is a fibre material which is wound around the longitudinal axis , wherein at least one portion of the fibre material assumes an angle relative to the longitudinal axis of between 40° and 50°, wherein the device is connected to the carrier structure system by means of the carrier element , and wherein the aircraft has a fuel cell which is connected to the at least three tanks via at least one line . <EOS>