Patent ID: 11919631
Assignee: ARCHER AVIATION, INC.
Field: Transport (Mechanical engineering)
Classification: CPC B | IPC B

Claim 0:
1. An electric vertical take-off and landing aircraft comprising:
a fuselage;
at least one tail extending from the fuselage;
a single wing that extends across the fuselage or a single pair of wings extending from each side of the fuselage, wherein the single wing or single pair of wings are the only wings of the aircraft;
a first plurality of proprotors mounted to the single wing or single pair of wings, positioned at least partially forward of a leading edge of the single wing or single pair of wings, and tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft;
a second plurality of proprotors mounted to the single wing or single pair of wings, positioned at least partially rearward of a trailing edge of the single wing or single pair of wings, and tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft, wherein each proprotor of the second plurality of proprotors has fewer blades that each proprotor of the first plurality of proprotors; and
a plurality of booms on each side of the fuselage that are mounted to the single wing or single pair of wings inward of ends of the single wing or single pair of wings, wherein each boom supports one proprotor of the first plurality of proprotors and one proprotor of the second plurality of proprotors, and wherein, for a respective boom, a rearward end of a respective proprotor of the first plurality of proprotors is pivotably mounted to a forward-most end of the respective boom and a forward end of a respective proprotor of the second plurality of proprotors is pivotably mounted to a rearward-most end of the respective boom, wherein a midpoint of each boom is mounted to the wing such that proprotors mounted to a respective boom are equidistant from the wing, and wherein the booms decrease in length from inward-most booms to outward-most booms such that:
an inward-most proprotor of the second plurality of proprotors is rearward of an outermost proprotor of the second plurality of proprotors, and
an inward-most proprotor of the first plurality of proprotors is forward of an outermost proprotor of the first plurality of proprotors,

wherein the first plurality of proprotors and the second plurality of proprotors are independently tiltable, and
wherein all propulsion available for the aircraft is provided by the first and second plurality of proprotors mounted to the single wing or single pair of wings.