Abstract: An overheat detection system comprising a controller for declaring the overheat, and two wiring connections running along a monitored system and configured to react upon overheat. The controller is configured to determine an electrical status of each wiring connection at least between operative and inoperative, the inoperative status corresponding to an electrical anomaly thereof, and electrically connect or disconnect the wiring connections depending on the electrical status thereof, wherein the declaration of overheat is based on a dynamic reconfiguration of the overheat detection system.

Abstract: A fuel cell system for an aircraft includes at least one fuel cell having a first inlet for providing a fuel, a second inlet for providing an oxidant, an outlet for removing exhaust air and a voltage outlet, an electrically operable hydraulic pump, which is integratable into a hydraulics network of the aircraft and connectable to the voltage outlet of the at least one fuel cell and a controllable hydraulic energy converter with changeable operating behaviour. The hydraulic energy converter is adapted for generating such a power demand in the hydraulics network, that the at least one fuel cell provides a predetermined volume flow of oxygen depleted air at the outlet through delivering electrical power to the hydraulic pump.

Abstract: An emergency power supply system for providing hydraulic power and electric power in an aircraft includes a fuel cell having an electric outlet for providing electric power, a conversion unit couplable with at least one of an AC bus and a DC bus and the electric outlet, and at least one hydraulic pump having a reconfigurable electric motor and a motor control unit and being couplable with a hydraulic system for providing hydraulic power. The conversion unit is adapted for converting a supply voltage of the electrical outlet to at least one of an AC voltage matching a predetermined voltage at the AC bus and a DC voltage matching a predetermined voltage at the DC bus. The reconfigurable electric motor is couplable with the fuel cell and the AC bus and is adapted for being operated by the supply of electric power either from the fuel cell or the AC bus.

Abstract: A fuel cell system for an aircraft includes a fuel cell, wherein at the cathode side a cathode inlet and a cathode outlet is provided, and wherein at the anode side an anode inlet and an anode outlet is provided, and a cathode recirculation channel for passing the cathode product fluid from the cathode outlet to the cathode inlet. In the fuel cell system, the water content of the cathode product fluid in the cathode recirculation channel can be reduced or at least stabilized in a possibly effective way, because the cathode recirculation channel includes a water extraction device for extracting water from the cathode product fluid.

Abstract: An overheat detection system comprising a controller for declaring the overheat, and two wiring connections running along a monitored system and configured to react upon overheat. The controller is configured to determine an electrical status of each wiring connection at least between operative and inoperative, the inoperative status corresponding to an electrical anomaly thereof, and electrically connect or disconnect the wiring connections depending on the electrical status thereof, wherein the declaration of overheat is based on a dynamic reconfiguration of the overheat detection system.

Abstract: A fuel cell system for an aircraft includes a fuel cell, wherein at the cathode side a cathode inlet and a cathode outlet is provided, and wherein at the anode side an anode inlet and an anode outlet is provided, and a cathode recirculation channel for passing the cathode product fluid from the cathode outlet to the cathode inlet. In the fuel cell system, the water content of the cathode product fluid in the cathode recirculation channel can be reduced or at least stabilized in a possibly effective way, because the cathode recirculation channel includes a water extraction device for extracting water from the cathode product fluid.

Abstract: A fuel cell system for an aircraft includes a fuel cell, wherein at the cathode side a cathode inlet and a cathode outlet is provided, and wherein at the anode side an anode inlet and an anode outlet is provided, and a cathode recirculation channel for passing the cathode product fluid from the cathode outlet to the cathode inlet. In the fuel cell system, the water content of the cathode product fluid in the cathode recirculation channel can be reduced or at least stabilized in a possibly effective way, because the cathode recirculation channel includes a water extraction device for extracting water from the cathode product fluid.

Abstract: A fuel cell system for an aircraft includes at least one fuel cell having a first inlet for providing a fuel, a second inlet for providing an oxidant, an outlet for removing exhaust air and a voltage outlet, an electrically operable hydraulic pump, which is integratable into a hydraulics network of the aircraft and connectable to the voltage outlet of the at least one fuel cell and a controllable hydraulic energy converter with changeable operating behaviour. The hydraulic energy converter is adapted for generating such a power demand in the hydraulics network, that the at least one fuel cell provides a predetermined volume flow of oxygen depleted air at the outlet through delivering electrical power to the hydraulic pump.

Abstract: An emergency power supply system for providing hydraulic power and electric power in an aircraft includes a fuel cell having an electric outlet for providing electric power, a conversion unit couplable with at least one of an AC bus and a DC bus and the electric outlet, and at least one hydraulic pump having a reconfigurable electric motor and a motor control unit and being couplable with a hydraulic system for providing hydraulic power. The conversion unit is adapted for converting a supply voltage of the electrical outlet to at least one of an AC voltage matching a predetermined voltage at the AC bus and a DC voltage matching a predetermined voltage at the DC bus. The reconfigurable electric motor is couplable with the fuel cell and the AC bus and is adapted for being operated by the supply of electric power either from the fuel cell or the AC bus.

Abstract: A fuel cell system for an aircraft includes a fuel cell, wherein at the cathode side a cathode inlet and a cathode outlet is provided, and wherein at the anode side an anode inlet and an anode outlet is provided, and a cathode recirculation channel for passing the cathode product fluid from the cathode outlet to the cathode inlet. In the fuel cell system, the water content of the cathode product fluid in the cathode recirculation channel can be reduced or at least stabilized in a possibly effective way, because the cathode recirculation channel includes a water extraction device for extracting water from the cathode product fluid.