US 12,269,581 B2
Systems and methods for efficient cruise and hover in VTOL
Michael V. Ol, Pasadena, CA (US); and Morteza Gharib, Altadena, CA (US)
Assigned to TOOFON, INC., Pasadena, CA (US); and CALIFORNIA INSTITUTE OF TECHNOLOGY, Pasadena, CA (US)
Filed by California Institute of Technology, Pasadena, CA (US); and Toofon, Inc., Pasadena, CA (US)
Filed on Mar. 17, 2022, as Appl. No. 17/655,296.
Claims priority of provisional application 63/162,410, filed on Mar. 17, 2021.
Prior Publication US 2022/0297822 A1, Sep. 22, 2022
Int. Cl. B64C 13/20 (2006.01); B64C 11/46 (2006.01); B64C 29/00 (2006.01); B64C 39/08 (2006.01); B64U 10/20 (2023.01); B64U 30/10 (2023.01); B64U 30/24 (2023.01); B64U 30/295 (2023.01); B64U 50/13 (2023.01)
CPC B64C 13/20 (2013.01) [B64C 11/46 (2013.01); B64C 29/0025 (2013.01); B64C 39/08 (2013.01); B64U 30/295 (2023.01); B64U 10/20 (2023.01); B64U 30/10 (2023.01); B64U 30/24 (2023.01); B64U 50/13 (2023.01); B64U 2201/10 (2023.01); B64U 2201/20 (2023.01)] 20 Claims
OG exemplary drawing
 
1. A multi-rotor vehicle comprising:
a body structure,
at least two main rotors connected to the body structure wherein the at least two main rotors are symmetrically disposed about a symmetry plane of the multi-rotor vehicle having at least one propeller and wherein each of the at least two main rotors are configured to generate lift for the multi-rotor vehicle;
at least one auxiliary rotor connected to the body structure disposed centrally along the symmetry plane being separated from the at least two main rotors by a distance greater than a diameter of the at least two main rotors such that a downwash from the at least two main rotors and a downwash from the at least one auxiliary rotor does not interfere;
at least two horizontal thrust rotors connected to the body structure and evenly disposed about the symmetry plane and configured to generate thrust in a forward direction such that a rotational plane of the at least two horizontal thrust rotors is perpendicular to a rotational plane of the at least two main rotors; and
at least one fixed wing element removably disposed on the body structure and configured to provide additional lift for the multi-rotor vehicle, the at least one fixed wing element comprising a wing planform spanning symmetrically across the symmetry plane and including at least one opening therein, the opening fully surrounding at least one of the at least one auxiliary rotor and the at least two main rotors to form a rotor-in-wing configuration, and wherein the other of at least one of the at least one auxiliary rotor and the at least two main rotors are partially enclosed by the wing planform of the at least one fixed wing element to form a partial in-wing rotor configuration, such that the at least one fixed wing element forms a shroud.