US 12,269,585 B2
Vertical take-off and landing aircraft
Robert W. Parks, San Jose, CA (US); Francesco Giannini, Falls Church, VA (US); Diana Siegel, Manassas, VA (US); and Jan D. Lienhard, Manhattan Beach, CA (US)
Assigned to BCG Digital Ventures GmbH, Berlin (DE)
Filed by BCG DIGITAL VENTURES GMBH, Berlin (DE)
Filed on Nov. 17, 2021, as Appl. No. 17/528,752.
Application 17/528,752 is a continuation of application No. 16/750,537, filed on Jan. 23, 2020, granted, now 11,208,203.
Application 16/750,537 is a continuation of application No. 15/494,780, filed on Apr. 24, 2017, granted, now 10,577,091, issued on Mar. 3, 2020.
Prior Publication US 2022/0258857 A1, Aug. 18, 2022
Int. Cl. B64C 27/26 (2006.01); B64C 27/30 (2006.01); B64C 29/00 (2006.01); B64C 39/08 (2006.01); B64C 39/12 (2006.01); B64D 27/24 (2006.01)
CPC B64C 27/26 (2013.01) [B64C 27/30 (2013.01); B64C 29/0025 (2013.01); B64C 39/08 (2013.01); B64C 39/12 (2013.01); B64D 27/24 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A vertical take-off and landing (VTOL) aircraft comprising:
a fuselage having a roll axis, the fuselage comprising a tensile stressed skin;
a thrust rotor to produce a propulsion thrust;
first and second rotor booms;
first and second canard surfaces, each of said first and second canard surfaces having a canard proximal end and a canard distal end connected to one of the first rotor boom or the second rotor boom and the fuselage;
first and second wing surfaces, each of said first and second wing surfaces having a wing proximal end and a wing distal end, a wing proximal end of the first wing surface being connected to a first side of the fuselage and a wing proximal end of the second wing surface being connected to a second side of the fuselage opposite the first side of the fuselage;
first and second tail surfaces, each of said first and second tail surfaces having a tail proximal end connected to one of the first and the second rotor booms and a tail distal end spaced apart from a tail distal end of the other tail surface;
a first plurality of lift rotors connected to the first rotor boom and a second plurality of lift rotors connected to the second rotor boom to produce lifting thrust force;
wherein the first and second rotor booms are positioned a distance below a plane defined by the lower surface of the fuselage, wherein the distance is defined by a length of the first and second canard surfaces.