CPC B64D 27/24 (2013.01) [B64C 1/16 (2013.01); B64D 2027/026 (2013.01); B64D 2221/00 (2013.01)] | 22 Claims |
1. An aircraft comprising:
a fuselage defining a longitudinal axis between a forward end and an aft end;
an airfoil extending laterally from the fuselage; and
an electrical system configured to power an electric motor of a hybrid electric propulsion system, the electrical system including:
an electric storage and an electric-motor controller electrically connected to the electric storage, wherein the electric-motor controller is positioned on or in the fuselage and wherein the electric storage is positioned within the fuselage; and
at least one conductor configured to extend from the electric storage to the electric motor to electrically connect the electric storage and the electric motor, wherein the at least one conductor follows a circumferential curvature of the fuselage, wherein at least one conductor of the at least one conductor extends from the electric storage up a first side of a cabin wall circumferentially about the longitudinal axis of the fuselage to the electric motor controller, wherein at least one conductor of the at least one conductor extends from the electric motor controller to the electric motor in a direction perpendicular to the longitudinal axis.
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