CPC B64D 31/10 (2013.01) [B64C 29/0025 (2013.01); B64C 29/0033 (2013.01); B64D 27/24 (2013.01)] | 17 Claims |
1. An electric aircraft, wherein the electric aircraft comprises:
a fuselage;
a plurality of laterally extending elements secured to the fuselage;
a plurality of lift components attached to the plurality of laterally extending elements, wherein each of the plurality of lift components has an adjustable lift angle with respect to a vertical axis, and wherein the plurality of lift components comprises:
a first set of lift components positioned in front of the center of gravity of the aircraft; and
a second set of lift components positioned to the rear of the center of gravity of the aircraft, wherein the second set of lift components is configured to rotate in a counterclockwise direction; and
at least a longitudinal thrust component attached to the plurality of laterally extending elements by a vertically aligned arm configured to secure the longitudinal thrust component to the laterally extending elements at a vertically offset distance, wherein the longitudinal thrust component is configured to generate a yaw force, wherein the longitudinal thrust component is located along a longitudinal axis of the electric aircraft central gravity located below the electric aircraft; and
a flight controller communicatively connected to a sensor,
wherein the sensor is configured to detect a rotation degradation associated with a failure event of a malfunctioning lift component resulting in a yaw torque causing a loss of control in the yaw axis; and
wherein the flight controller is configured to adjust the lift angle of one or more of the plurality of lift components to eliminate the yaw torque.
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