Patent ID: 9315252
Filing Date: 2016-04-19
CPC Classification: B64C,Y10T

Claim Text:
1. A composite for an aircraft or spacecraft, comprising: a skin portion; a stringer which is attached to the skin portion, wherein the stringer is constructed in a T-shape and comprises a foot portion and a web portion, wherein the foot portion and the web portion each form a closed wall; and a former made from fibre composite material, which is attached to the skin portion and forms an opening therewith, through which the stringer extends completely with the foot portion and the web portion, substantially transverse to the former, wherein the only material disposed within the former is the transversely positioned stringer, wherein the former is constructed as a hollow Ω-profile with closed side-walls, wherein each of the closed side-walls is provided with the opening through which the stringer extends completely with its foot portion and its web portion, wherein a foot portion of the former is side by side with the foot portion of the stringer, and wherein the stringer is arranged to contact the skin portion and is riveted to the skin portion, but not fixed to the former.