| CPC B64D 27/32 (2024.01) [B64C 29/00 (2013.01); B64D 27/30 (2024.01); B64D 27/31 (2024.01); B64D 27/33 (2024.01); B64D 27/35 (2024.01); B64D 2221/00 (2013.01)] | 6 Claims |
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1. An aircraft comprising:
a wing attached to a fuselage and configured to generate lift;
a generator configured to generate electric power;
an engine configured to drive the generator;
a first rotor configured to generate thrust in a vertical direction;
a second rotor configured to generate thrust in the vertical direction;
a first electric motor configured to drive the first rotor;
a second electric motor configured to drive the second rotor;
a first harness that is at least partially wired inside the wing and is configured to transmit the electric power generated by the generator to the first electric motor; and
a second harness that is at least partially wired inside the wing and is configured to transmit the electric power generated by the generator to the second electric motor,
wherein the engine is arranged in a manner so that the engine overlaps the wing in a front-rear direction of the fuselage,
the first harness and the second harness are arranged inside the wing so as to be separated from each other in the front-rear direction of the fuselage,
inside the wing, a front spar, a middle spar, and a rear spar are provided in order of the front spar, the middle spar, and the rear spar from a front side of the fuselage in the front-rear direction of the fuselage,
the first harness is disposed between the front spar and the middle spar in the front-rear direction of the fuselage, and
the second harness is disposed between the middle spar and the rear spar in the front-rear direction of the fuselage.
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