Aircraft comprises a heater system, a conduit system thermally connected to fuel cell stacks, a pump system, and a controller. The heater system is configured to heat a coolant. The coolant flows through the conduit system. The pump system is configured to circulate the coolant through the conduit system to the fuel cell stacks. The controller is configured to control the heater system to heat the coolant to form a heated coolant. The controller is configured to control the pump system to circulate the heated coolant through the conduit system. The controller is configured to control the conduit system to circulate the heated coolant to a subset of the fuel cell stacks, wherein the heated coolant causes the subset of the fuel cell stacks to reach an operating temperature.
Start-Up of High Temperature Proton Exchange Membrane (HTPEM) Fuel Cell Aircraft with Multiple Power Generating Units
20.02.2025
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B60L PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES , Antrieb von elektrisch angetriebenen Fahrzeugen / H01M Verfahren oder Mittel, z.B. Batterien, für die direkte Umwandlung von chemischer in elektrische Energie , PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY |
Europäisches Patentamt | 2025
|Europäisches Patentamt | 2025
|Europäisches Patentamt | 2025
|Maximum power cold start mode of proton exchange membrane fuel cell
Tema Archiv | 2014
|Assessment of a Serial Cooling Concept for HTPEM Fuel Cell Systems for Aviation Applications
Deutsches Zentrum für Luft- und Raumfahrt (DLR) | 2022
|