US 12,384,517 B2
Aircraft wing unit with pressure fence
Michael Murphy, Whitby (CA); Jack Araujo, Ajax (CA); Gary Shum, Mississauga (CA); and George Bradley, Montreal (CA)
Assigned to BOMBARDIER INC., Dorval (CA)
Filed by BOMBARDIER INC., Dorval (CA)
Filed on Dec. 27, 2023, as Appl. No. 18/398,013.
Application 18/398,013 is a continuation of application No. 16/608,978, granted, now 11,891,173, previously published as PCT/IB2018/052906, filed on Apr. 26, 2018.
Claims priority of provisional application 62/492,583, filed on May 1, 2017.
Prior Publication US 2024/0124120 A1, Apr. 18, 2024
Int. Cl. B64C 3/58 (2006.01); B64C 1/06 (2006.01); B64C 1/26 (2006.01); B64F 5/10 (2017.01)
CPC B64C 3/58 (2013.01) [B64C 1/26 (2013.01); B64F 5/10 (2017.01); B64C 1/06 (2013.01)] 5 Claims
OG exemplary drawing
 
1. A method for producing an aircraft structural assembly using a fuselage portion partially defining a pressure vessel and an assembled wing unit wherein the assembled wing unit comprises: a first wing extending in a first lateral direction relative to the fuselage portion and a second wing extending in an opposite second lateral direction relative to the fuselage portion; a first pressure fence attached to the first wing; and a second pressure fence attached to the second wing, the method comprising:
assembling the assembled wing unit with the fuselage portion so that the first pressure fence defines a first part of the pressure vessel partially defined by the fuselage portion and the second pressure fence defines a second part of the pressure vessel partially defined by the fuselage portion,
wherein:
the fuselage portion comprises a fuselage skin supported by a fuselage frame;
the first pressure fence comprises a first fence skin and the second pressure fence comprises a second fence skin;
the second fence skin extends upwardly relative to an upper wing skin of the second wing and also in the second lateral direction
the assembling the assembled wing unit with the fuselage portion includes:
abutting a first surface of an upper portion of the first fence skin with a portion of a surface of the fuselage skin forming a first contact area;
abutting a portion of a second surface of the upper portion of the first fence skin with a portion of a surface of the fuselage frame of the fuselage portion forming a second contact area, the second contact area being at an angle from the first contact area; and
using the upper portion of the first fence skin extending upwardly to guide the fuselage frame for self-alignment in the first or second lateral direction between the fuselage portion and the first pressure fence.