The invention relates to an aircraft, in particular to an airplane, having at least one fuel cell, having at least one supply line which connects the fuel cell to a fuel supply, having at least one outlet line by means of which fuel supplied by the supply line and not consumed in the fuel cell is drained off and having means for the influencing of the fuel flow through the fuel cell.
The use of fuel cells in aeronautics is known. The fuel cells deliver electrical energy which can be utilized to drive different components of an aircraft. The advantage of the use of fuel cells is an efficiency which is improved with respect to conventional systems with reduced pollution and noise emissions. In fuel cells known from the art, the supply of the fuels to the fuel cell takes place by means of supply lines which are in connection with a corresponding fuel supply. In this process, flow regulators, generally so-called mass flow controllers, are located in the supply lines and ensure the desired fuel flow through the anode side and the cathode side of the fuel cell. The disadvantage of such flow regulators is a comparatively high proneness to defects and the technical regulation effort associated with their use.