US 11,772,789 B2
Tail sitter
Riccardo Bianco Mengotti, Samarate (IT)
Assigned to LEONARDO S.P.A., Rome (IT)
Appl. No. 16/973,307
Filed by LEONARDO S.P.A., Rome (IT)
PCT Filed Jun. 28, 2019, PCT No. PCT/IB2019/055514
§ 371(c)(1), (2) Date Dec. 8, 2020,
PCT Pub. No. WO2020/003239, PCT Pub. Date Jan. 2, 2020.
Claims priority of application No. 18180581 (EP), filed on Jun. 28, 2018.
Prior Publication US 2021/0245875 A1, Aug. 12, 2021
Int. Cl. B64C 29/02 (2006.01); B64C 9/00 (2006.01); B64C 25/32 (2006.01); B64C 27/54 (2006.01); B64C 39/02 (2023.01); B64C 39/06 (2006.01); B64U 10/00 (2023.01)
CPC B64C 29/02 (2013.01) [B64C 9/00 (2013.01); B64C 25/32 (2013.01); B64C 27/54 (2013.01); B64C 39/024 (2013.01); B64C 39/068 (2013.01); B64C 2009/005 (2013.01); B64U 10/00 (2023.01)] 13 Claims
OG exemplary drawing
 
1. A tail sitter aircraft (1′, 1″″) comprising: a wing (4) with a closed front section (C);
a fuselage (2), from which said wing (4) extends; said fuselage (2) extending parallel to a first axis (Y);
said wing (4) being a non-planar wing closed in on itself and without free ends; said front section (C) being defined by the projection of said wing (4) on a plane orthogonal to said first axis (Y);
said wing (4) comprising:
a first portion (5) projecting from said fuselage (2);
a second portion (6) spaced from said first portion (5); and
a first and a second connecting section (7), which are interposed between respective ends (8, 9) of said first portion (5) and of said second portion (6);
said first portion (5) and said second portion (6) being parallel to one another and extending parallel to a second axis (X) orthogonal to said first axis (Y);
said first axis (Y) being arranged, in use, vertically in a take-off/landing position and inclined with respect to the vertical direction in a cruising position;
characterized in that said first and a second connecting section (7) extend parallel to a third axis (Z) orthogonal to said second axis (X) and to said first axis (Y);
said wing (4) with a closed front section (C) comprising a third portion (30) arranged on the opposite side of said first portion (5) with respect to said second portion (6) and connected to said first portion (5) at their respective ends (32, 8) by first sections (31) extending parallel to said third axis (Z);
wherein a centre section of said third portion (30) is connected to said fuselage (2) by second sections (33) interposed between first sections (31) along said second axis (X).