US 11,053,000 B2
Aerodyne with vertical-takeoff-and-landing ability
Jesús Carlos Castellano Aldave, Navarra (ES); Jesus Villadangos Alonso, Navarra (ES); José Javier Astrain Escola, Navarra (ES); Carlos Matilla Codesal, Madrid (ES); Mael Taleb, Navarra (ES); Tania Jorajuría Gomez, Navarra (ES); and Ermö Peter Cosma, Madrid (ES)
Appl. No. 15/773,785
Filed by FUVEX SISTEMAS, S.L., Navarra (ES); and UNIVERSIDAD PÚBLICA DE NAVARRA, Navarra (ES)
PCT Filed Oct. 14, 2016, PCT No. PCT/ES2016/000112
§ 371(c)(1), (2) Date Aug. 21, 2018,
PCT Pub. No. WO2017/077144, PCT Pub. Date May 11, 2017.
Claims priority of application No. P201531579 (ES), filed on Nov. 4, 2015.
Prior Publication US 2019/0152593 A1, May 23, 2019
Int. Cl. B64C 27/28 (2006.01); B64C 29/00 (2006.01); B64C 27/26 (2006.01); B64C 27/37 (2006.01)
CPC B64C 27/28 (2013.01) [B64C 27/26 (2013.01); B64C 27/37 (2013.01); B64C 29/0016 (2013.01); B64C 29/0033 (2013.01)] 18 Claims
OG exemplary drawing
 
1. An aerodyne with vertical take-off and landing ability and an ability to generate lift by means of both rotors and fixed wings, said aerodyne including:
a fuselage defining a longitudinal axis, a transverse axis, and a vertical axis orthogonal to one another;
at least two fixed wings arranged symmetrically on opposite sides of the fuselage, providing two lifting surfaces that are sufficient to keep the aerodyne airborne as it moves forward through the air in direction parallel to the longitudinal axis;
at least two front rotors and at least two rear rotors arranged symmetrically on two opposite sides of the fuselage and actuated by means of independent motors;
each rotor defines an axis of rotation and is connected to a support pivotally connected to a connection shaft parallel to the transverse axis of the fuselage placed in a central portion of one of the fixed wings;
the rotors are actuated to transition during flight, through said pivotal connection, from a lift position with the axes of rotation of the rotors parallel to the vertical axis of the fuselage, providing lift sufficient to keep the aerodyne airborne, to a longitudinal forward movement position with the axes of rotation parallel to the longitudinal axis of the fuselage, propelling the aerodyne through the air in the direction parallel to the longitudinal axis, or to transition from the forward movement position to the lift position;
the front rotors are arranged in front of a leading edge of the fixed wings in the lift position, and below the fixed wings in the longitudinal forward movement position; and
the rear rotors are arranged behind the leading edge of the fixed wings in the lift position, and above the fixed wings in the longitudinal forward movement position;
in the lift position, said rear rotors partially overlap with a portion of the wing to which they are attached;
each fixed wing includes at least one flap in the portion of the fixed wing overlapped by the rear rotor when in the lifting position, said at least one flap is freely connected to the rest of the wing, and is free aerodynamically orientable under an influence of an airflow striking the at least one flap, produced by the rotors in the lift position, in the longitudinal forward movement position and in intermediate positions, and by gravity, the at least one flap transitioning between a lift position parallel to the vertical axis and a longitudinal forward movement position parallel to the longitudinal axis.