Aircraft comprises a heater system (1901), a conduit system (1902, 2990) thermally connected to fuel cell stacks (1920), a pump system (1904), and a controller (1905). The heater system (1901) is configured to heat a coolant (1917). The coolant (1917) flows through the conduit system (1902, 2990). The pump system (1904) is configured to circulate the coolant (1917) through the conduit system (1902, 2990) to the fuel cell stacks (1920). The controller (1905) is configured to control the heater system (1901) to heat the coolant (1917) to form a heated coolant (1916). The controller (1905) is configured to control the pump system (1904) to circulate the heated coolant (1916) through the conduit system (1902, 2990). The controller (1905) is configured to control the conduit system (1902, 2990) to circulate the heated coolant (1916) to a subset of the fuel cell stacks (1920), wherein the heated coolant (1916) causes the subset of the fuel cell stacks (1920) to reach an operating temperature (1925).
START-UP OF HIGH TEMPERATURE PROTON EXCHANGE MEMBRANE (HTPEM) FUEL CELL AIRCRAFT WITH MULTIPLE POWER GENERATING UNITS
START EINES HOCHTEMPERATUR-PROTONENAUSTAUSCHMEMBRAN (HTPEM)-BRENNSTOFFZELLENFLUGZEUGS MIT MEHREREN STROMERZEUGUNGSEINHEITEN
DÉMARRAGE D'UN AÉRONEF À PILE À COMBUSTIBLE À MEMBRANE ÉCHANGEUSE DE PROTONS À HAUTE TEMPÉRATURE (HTPEM) DOTÉ DE MULTIPLES UNITÉS DE GÉNÉRATION D'ÉNERGIE
07.05.2025
Patent
Elektronische Ressource
Englisch
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