US 12,459,221 B2
Method for producing a torsion box for a structure of an airplane and a torsion box for a structure of an airplane
Claas De Jong, Stade (DE); and René Schröder, Buxtehude (DE)
Assigned to Airbus Operations GmbH, Hamburg (DE)
Filed by Airbus Operations GmbH, Hamburg (DE)
Filed on Nov. 26, 2021, as Appl. No. 17/535,885.
Application 17/535,885 is a continuation of application No. PCT/IB2020/000903, filed on Aug. 31, 2020.
Claims priority of application No. 10 2019 123 012.8 (DE), filed on Aug. 28, 2019.
Prior Publication US 2022/0080686 A1, Mar. 17, 2022
Int. Cl. B64C 1/06 (2006.01); B29C 65/02 (2006.01); B29C 65/48 (2006.01); B29C 65/60 (2006.01); B29D 24/00 (2006.01); B64C 3/18 (2006.01); B64F 5/10 (2017.01)
CPC B29D 24/008 (2013.01) [B29C 65/022 (2013.01); B29C 65/48 (2013.01); B29C 65/60 (2013.01); B64C 1/064 (2013.01); B64C 1/065 (2013.01); B64C 3/185 (2013.01); B64C 3/187 (2013.01); B64F 5/10 (2017.01)] 17 Claims
OG exemplary drawing
 
1. A method for manufacturing a torsion box for a structure of an aircraft, the method comprising:
forming a first component by:
providing a first flat base with a first flat inner side and a first outer side; and
welding multiple first stiffening elements onto and in direct contact with the first flat inner side of the first flat base to form with the first flat base a one-piece composite component, wherein the first stiffening elements comprise multiple longitudinally extending ribs that have a same profile or shape as the first flat inner side of the first flat base;
wherein the first flat base and the multiple first stiffening elements are made of a fiber composite material comprising a fabric impregnated with a resin as a matrix material; and
wherein the first flat inner side has a same flat shape as the first outer side;
forming a second component by:
providing a second flat base with a second flat inner side and a second outer side; and
welding multiple second stiffening elements onto the second flat inner side of the second flat base to form with the second flat base a one-piece composite component, wherein the second stiffening elements comprise multiple longitudinally extending spars that have a same profile or shape as the second flat inner side of the second flat base;
wherein the second flat base and the multiple second stiffening elements are made of a fiber composite material comprising a fabric impregnated with a resin as a matrix material;
superimposing the first component and the second component such that the first stiffening elements lie, at least in some areas, on the second flat inner side and the second stiffening elements lie, at least in some areas, directly on the first flat inner side;
connecting the first stiffening elements to the second flat base; and
connecting the second stiffening elements directly to the first flat base;
wherein the multiple longitudinally extending ribs extend in a first direction, the multiple longitudinally extending spars extend in a second direction, and the first direction is transverse to the second direction;
wherein each of the longitudinally extending ribs are formed as discontinuous elements that are separated from each other in the first direction by one of a plurality of gaps, such that each of the discontinuous elements does not touch any of the other discontinuous elements of a same one of the longitudinally extending ribs;
wherein the longitudinally extending spars extend through a corresponding one of the plurality of gaps; and
wherein the first direction is a chord direction of the torsion box and the second direction is a wingspan direction of the torsion box.