Abstract: The present disclosure relates to a valve, preferably a continuous valve comprising a spool and a spool sleeve, wherein the spool comprises a control surface and the spool sleeve comprises an opening, wherein the valve is configured in such a way that the control surface can cover the opening, wherein the spool can be positioned such that the control surface at least partially does not cover the opening, wherein the spool sleeve comprises a further opening, wherein the control surface can cover the further opening, wherein the spool can be positioned such that the control surface at least partially does not cover each of the opening and the further opening.

Abstract: The present invention relates to an emergency power system for an aircraft having at least one fuel cell unit for producing electric power, wherein the fuel cell unit is cooled via at least one cooling circuit which includes at least one heat exchanger, and wherein the heat exchanger is connected to at least one air distribution system of the aircraft cabin so that exhaust air heated by the heat exchanger in the operation of the emergency power system can be distributed via the air distribution system in the aircraft cabin.

Abstract: The present invention relates to an emergency power system for an aircraft having at least one fuel cell unit for producing electric power, wherein the fuel cell unit is cooled via at least one cooling circuit which includes at least one heat exchanger, and wherein the heat exchanger is connected to at least one air distribution system of the aircraft cabin so that exhaust air heated by the heat exchanger in the operation of the emergency power system can be distributed via the air distribution system in the aircraft cabin.

Abstract: 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 as well as having means for the influencing of the fuel flow through the fuel cell, with the means for the influencing of the fuel flow having a pressure regulator located in the at least one supply line and a restrictor member located in the at least one outlet line, with the pressure regulator regulating the pressure of the fuel supply to the operating pressure of the fuel cell and with the restrictor member reducing the flow of the fuel flowing through the outlet line.

Abstract: 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 as well as having means for the influencing of the fuel flow through the fuel cell, with the means for the influencing of the fuel flow having a pressure regulator located in the at least one supply line and a restrictor member located in the at least one outlet line, with the pressure regulator regulating the pressure of the fuel supply to the operating pressure of the fuel cell and with the restrictor member reducing the flow of the fuel flowing through the outlet line.