US 12,448,124 B2
Aerial vehicles, cooperative flying systems, and methods of operating the same
Gary E. Georgeson, Tacoma, WA (US); and Joseph L. Hafenrichter, Seattle, WA (US)
Assigned to The Boeing Company, Arlington, VA (US)
Filed by The Boeing Company, Arlington, VA (US)
Filed on Dec. 13, 2023, as Appl. No. 18/538,179.
Application 18/538,179 is a division of application No. 17/503,537, filed on Oct. 18, 2021, abandoned.
Claims priority of provisional application 63/127,568, filed on Dec. 18, 2020.
Prior Publication US 2024/0109651 A1, Apr. 4, 2024
Int. Cl. B64C 29/02 (2006.01); B64C 3/38 (2006.01); B64C 9/26 (2006.01); B64C 27/22 (2006.01); B64C 27/32 (2006.01); B64C 27/54 (2006.01); B64D 31/06 (2006.01); B64U 10/20 (2023.01); B64U 30/10 (2023.01); B64U 30/24 (2023.01); B64U 30/26 (2023.01); B64U 50/31 (2023.01)
CPC B64C 29/02 (2013.01) [B64C 3/38 (2013.01); B64C 3/385 (2013.01); B64C 9/26 (2013.01); B64C 27/22 (2013.01); B64C 27/32 (2013.01); B64C 27/54 (2013.01); B64D 31/06 (2013.01); B64U 10/20 (2023.01); B64U 30/10 (2023.01); B64U 30/24 (2023.01); B64U 30/26 (2023.01); B64U 50/31 (2023.01); B64U 2201/00 (2023.01)] 20 Claims
OG exemplary drawing
 
1. An aerial vehicle comprising:
a wing body having an airfoil shape and comprising:
a wing first section;
a wing second section, opposite the wing first section along a first vehicle axis;
a first wingtip and a second wingtip, located opposite the first wingtip along the first vehicle axis; and
a first edge and a second edge, located opposite the first edge along a second vehicle axis, perpendicular to the first vehicle axis;
a first coaxial rotor configured to rotate in a first rotational direction about the second vehicle axis;
second coaxial rotor configured to rotate in a second rotational direction, opposite to the first rotational direction, about the second vehicle axis;
a drive assembly positioned between the wing first section and the wing second section and configured to rotate the first coaxial rotor and the second coaxial rotor; and
a controller configured to selectively control thrust produced by the first coaxial rotor and the second coaxial rotor,
wherein:
the wing first section and the wing second section are rotatable about the first vehicle axis relative to the drive assembly;
selective control of the thrust produced by the first coaxial rotor and the second coaxial rotor induces a pitch motion of the aerial vehicle to transition the aerial vehicle between a horizontal flight state and a vertical flight state;
in the horizontal flight state, the second vehicle axis is approximately horizontal and a collective thrust from the first coaxial rotor and the second coaxial rotor is directed forward; and
in the vertical flight state, the second vehicle axis is approximately vertical and the collective thrust from the first coaxial rotor and the second coaxial rotor is directed upward.