An aircraft electric power system (1, 1A) provided in an aircraft (100) includes a predetermined DC power supply bus (11, 14) for supplying electric power to a load (31, 41, 41', 51). The DC power supply bus (11, 14) is configured to always be connected to two or more types of power supply devices (21, 22, 23, 27) as e.g. a main power unit (21, 22,23) driven by an enginge (103L, 103R) for applying a thrust force to the aircraft or another power supply device (27,27a) including an electricity storaghe device (27,27a).
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