Method for producing a torsion box for a structure of an airplane and a torsion box for a structure of an airplane

A torsion box for a structure of an aircraft, the torsion box comprising:

• a first component comprising:
• a first flat base with a first flat inner side and a first outer side;
• and
• multiple first stiffening elements that are welded 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;
• wherein the first flat inner side has a same flat shape as the first outer side;
• and
• a second component comprising:
• a second flat base with a second flat inner side and a second outer side;
• and
• multiple second stiffening elements that are welded 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;
• wherein the first flat base and the second flat base are superimposed 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;
• wherein the first stiffening elements and the second flat base are connected to one another in a form-fitting, force-fitting, or substance-bonded manner;
• wherein the second stiffening elements and the first flat base are directly connected to one another in a form-fitting, force-fitting, or substance-bonded manner;
• 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.