Patent ID: 8091828

Claim:
A method for manufacturing a structural element intended for aeronautical construction, comprising a web extending substantially in a plane L,H, L being the longitudinal direction and H being the transverse direction, the web having a length L 1 and a height H 1 , the structural element being intended to be subjected to bending stress by a moment perpendicular to the said plane L,H, and one or more adjacent stringer elements which are substantially perpendicular to the web and which extend in the transverse direction, comprising the following steps (i) at least a first and second metal block are made available, the limit of elasticity under compression of the first metal block being greater than that of the second metal block, (ii) the first metal block is machined in such a manner as to obtain a first machined monolithic part S which comprises a first web portion having a length L 1 and a height H 4 less than H 1 and at least one stringer element which is substantially perpendicular and adjacent to the first web portion and whose height H′ 1 , which is substantially equal to H 1 , is such that a stringer portion of height H′ 1 -H 4 extends beyond the first web portion, (iii) there is prepared, by shaping the second metal block, at least one second part T comprising at least a second web portion of length L 1 and height H 5 extending in the direction of the height H up to a height H 5 , such that the sum H 4 +H 5 is substantially equal to H 1 , (iv) the first monolithic part S and the second part T are assembled by placing the web portions end-to-end over their entire common length L 1 , so that the stringer portion is adjacent to the second web portion.