US 11,745,886 B2
Electric aircraft for generating a yaw force
Nicholas Moy, Burlington, VT (US); Riley Griffin, Montpelier, VT (US); Lochie Ferrier, Sydney (AU); and Collin Freiheit, Burlington, VT (US)
Assigned to BETA AIR, LLC, South Burlington, VT (US)
Filed by BETA AIR, LLC, South Burlington, VT (US)
Filed on Jun. 29, 2021, as Appl. No. 17/361,497.
Prior Publication US 2022/0411089 A1, Dec. 29, 2022
Int. Cl. B64D 31/10 (2006.01); B64D 27/24 (2006.01); B64C 29/00 (2006.01)
CPC B64D 31/10 (2013.01) [B64C 29/0025 (2013.01); B64C 29/0033 (2013.01); B64D 27/24 (2013.01)] 17 Claims
OG exemplary drawing
 
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.