US 12,486,030 B2
Vertical take-off and landing aerodyne optimized for horizontal flight
Gérard Tavin, Angers (FR)
Appl. No. 18/257,462
Filed by Gérard Tavin, Angers (FR)
PCT Filed Dec. 10, 2021, PCT No. PCT/IB2021/061586
§ 371(c)(1), (2) Date Jun. 14, 2023,
PCT Pub. No. WO2022/130151, PCT Pub. Date Jun. 23, 2022.
Claims priority of application No. 2013207 (FR), filed on Dec. 14, 2020.
Prior Publication US 2024/0025540 A1, Jan. 25, 2024
Int. Cl. B64C 29/00 (2006.01); B64C 1/30 (2006.01); B64C 3/56 (2006.01); B64C 27/12 (2006.01); B64C 27/30 (2006.01); B64D 35/024 (2025.01)
CPC B64C 29/0025 (2013.01) [B64C 1/30 (2013.01); B64C 3/56 (2013.01); B64C 27/30 (2013.01); B64C 27/12 (2013.01); B64D 35/024 (2024.01)] 23 Claims
OG exemplary drawing
 
1. A vertical take-off and landing aerodyne comprising:
a fuselage;
two wings configured to provide lift in horizontal flight;
a direction and fore-and-aft controller;
a horizontal flight propulsion system comprising
a counter-rotating propeller disposed at a tail of the aerodyne, and
a drive system configured to drive the counter-rotating propeller in rotation about an axis of rotation, the counter-rotating propeller being configured to be oriented by the controller about two axes, one of said two axes being parallel to a yaw axis of the aerodyne and the other of said two axes being parallel to a pitch axis of the aerodyne, so that the counter-rotating propeller operates as a steering system configured to steer and stabilize the aerodyne during horizontal flight phases such that the aerodyne has no additional steering system configured to steer or stabilize the aerodyne during the horizontal flight phases at the tail; and
at least one pair of rotors configured to provide propulsion and lift in the take-off and landing phases, the rotors being retractable, each of the rotors being carried by an arm movable between: (i) an extended position, in which the rotor is located on a respective side of the fuselage, with an axis of rotation of the rotor being vertical, two rotors of the same pair of rotors being symmetrical in relation to a longitudinal axis of the fuselage, and (ii) a retracted position, in which the arm and the respective rotor are received in a housing of the fuselage.