US 12,337,966 B2
Methods for improvements of the closed wing aircraft concept and corresponding aircraft configurations
Andras Hernadi, Stockholm (SE)
Appl. No. 17/162,644
Filed by Andras Hernadi, Stockholm (SE)
PCT Filed Aug. 19, 2018, PCT No. PCT/SE2018/050835
§ 371(c)(1), (2) Date Jan. 29, 2021,
PCT Pub. No. WO2020/040671, PCT Pub. Date Feb. 27, 2020.
Prior Publication US 2022/0242565 A1, Aug. 4, 2022
Int. Cl. B64C 39/06 (2006.01); B64C 3/56 (2006.01)
CPC B64C 39/068 (2013.01) [B64C 3/56 (2013.01)] 4 Claims
OG exemplary drawing
 
1. A method for improving a closed wing aircraft, the method comprising steps of:
designing an aircraft fuselage and designing three main wings on each side of the aircraft fuselage, namely a 1st wing, a 2nd wing and a 3rd wing, wherein: the 1st wing is backward swept which extends from a lower part of a front portion of the aircraft fuselage; the 2nd wing is dihedral, located horizontally behind and vertically above the 1st wing and structurally connected to an upper middle portion of the aircraft fuselage as a shoulder wing, a high wing or a parasol wing; the 3rd wing is forward swept, located horizontally behind and vertically above the 2nd wing and structurally interconnected to the aircraft fuselage in a way comprising at least one tail;
designing the 1st wing with an upward-bent tip section with a curved transition area;
designing the 2nd wing with an upward-bent tip section with a curved transition area;
designing a structural interconnection between the 1st wing and the 2nd wing comprising a bracing side-wing entity with its lower end connected to an upper end of the upward-bent tip section of the 1st wing, wherein an upper end of said bracing side-wing entity has an inward-bent tip section connected to the curved transition area of the upward-bent tip section of the 2nd wing, forming a bracing framework between the 1st wing and the 2nd wing which comprises a closed frame forming an aerodynamic channel;
designing a structural interconnection between the 2nd wing and the 3rd wing comprising a bracing wingtip-fence entity, interconnecting an upper end of the upward-bent tip section of the 2nd wing and a wingtip or a wingtip portion of the 3rd wing, forming a bracing framework between the 2nd wing and the 3rd wing which comprises a closed frame forming a corresponding aerodynamic channel, wherein said bracing wingtip-fence entity is different from the bracing side-wing entity;
f) designing the 3rd wing with an upward-bent root section with a curved transition area;
wherein, the structural interconnection between the 1st wing and the 2nd wing comprises a propulsion unit, wherein said propulsion unit is connected to the upper end of the upward-bent tip section of the 1st wing; and
wherein the structural interconnection between the 2nd wing and the 3rd wing comprises another propulsion unit, wherein said another propulsion unit is connected to the upper end of the upward-bent tip section of the 2nd wing.