US 11,811,114 B2
Power supply device and method thereof for fuel cell
Yin-Wen Tsai, Zhubei (TW); Chih-Wei Hsu, Zhudong Township (TW); Yuh-Fwu Chou, Zhubei (TW); Chin-Yi Shih, Hsinchu (TW); and Chien-Chi Chiu, Tainan (TW)
Assigned to INDUSTRIAL TECHNOLOGY RESEARCH INSTITUTE, Hsinchu (TW)
Filed by INDUSTRIAL TECHNOLOGY RESEARCH INSTITUTE, Hsinchu (TW)
Filed on Dec. 30, 2020, as Appl. No. 17/137,601.
Prior Publication US 2022/0209267 A1, Jun. 30, 2022
Int. Cl. H01M 8/04858 (2016.01); H01M 8/04664 (2016.01); B60L 58/40 (2019.01)
CPC H01M 8/04888 (2013.01) [B60L 58/40 (2019.02); H01M 8/04686 (2013.01); H01M 8/04917 (2013.01); H01M 8/04947 (2013.01); H01M 2250/20 (2013.01)] 21 Claims
OG exemplary drawing
 
1. A power supply device configured on an aircraft having an average required power value, wherein the power supply device comprises:
a secondary battery;
a transformer electrically connected between the secondary battery and the aircraft; and
a fuel cell electrically connected to the aircraft and suitable for providing a first output current to the aircraft; and
a bypass switch electrically connected between an output terminal of the secondary battery and an output terminal of the fuel cell and the bypass switch and connected in parallel with the transformer;
wherein, the transformer has a first output voltage set value, when a first output terminal voltage of the fuel cell is lower than the first output voltage set value and the bypass switch is in a non-conducting state, a second output current of the secondary battery is provided to the aircraft via the transformer; when the first output terminal voltage of the fuel cell is lower than the first output voltage set value and the bypass switch is in a conducting state, the second output current of the secondary battery is provided to the aircraft via the bypass switch;
wherein, the first output voltage set value is a corresponding voltage value of a power value in a power range between a maximum power value of a characteristic curve of the fuel cell and the average required power value of the aircraft.