A control device for an aircraft, the aircraft comprising: at least one first generator configured to generate electric power; at least one first battery (50a, 50b) configured to store electric power; at least one first electric motor (20V1_1, 20V4_1, 20V5_1, 20V8_1, 24C1_1, 24C3_1) configured to operate with electric power supplied from the first generator and the first battery; at least one second generator configured to generate electric power; at least one second battery (50c, 50d) configured to store electric power; at least one second electric motor (20V2_2, 20V3_2, 20V6_2, 20V7_2, 24C2_2, 24C4_2) configured to operate with electric power supplied from the second generator and the second battery; and a plurality of rotors (18V, 22C) configured to generate thrust acting on a fuselage, wherein the control device comprises an electric motor control section configured to control the first electric motor and the second electric motor, and wherein each of the rotors is driven by one of the first electric motor or the second electric motor, or both of the first electric motor and the second electric motor, characterised in that the electric motor control section is configured to, in a case that the electric motor control section determines that supply of electric power from the first generator to the first electric motor is unavailable and supply of electric power from the second generator to the second electric motor is available, reduce power consumption of the first electric motor by reducing thrust generated by the rotor driven by the first electric motor, and increase thrust generated by the rotor driven by the second electric motor, as compared with a case where the supply of the electric power from the first generator to the first electric motor is available and the supply of the electric power from the second generator to the second electric motor is available. at least one first generator configured to generate electric power; at least one first battery (50a, 50b) configured to store electric power; at least one first electric motor (20V1_1, 20V4_1, 20V5_1, 20V8_1, 24C1_1, 24C3_1) configured to operate with electric power supplied from the first generator and the first battery; at least one second generator configured to generate electric power; at least one second battery (50c, 50d) configured to store electric power; at least one second electric motor (20V2_2, 20V3_2, 20V6_2, 20V7_2, 24C2_2, 24C4_2) configured to operate with electric power supplied from the second generator and the second battery; and a plurality of rotors (18V, 22C) configured to generate thrust acting on a fuselage, wherein the control device comprises an electric motor control section configured to control the first electric motor and the second electric motor, and wherein each of the rotors is driven by one of the first electric motor or the second electric motor, or both of the first electric motor and the second electric motor, characterised in that the electric motor control section is configured to, in a case that the electric motor control section determines that supply of electric power from the first generator to the first electric motor is unavailable and supply of electric power from the second generator to the second electric motor is available, reduce power consumption of the first electric motor by reducing thrust generated by the rotor driven by the first electric motor, and increase thrust generated by the rotor driven by the second electric motor, as compared with a case where the supply of the electric power from the first generator to the first electric motor is available and the supply of the electric power from the second generator to the second electric motor is available.