Patent ID: 8528865

Claim:
A system comprising: a shell component of an aircraft or spacecraft: a T-stringer, wherein the T-stringer comprises a foot portion and a comb portion; an omega stringer, wherein the omega stringer comprises a hollow profile cross section with a comb portion and a foot portion, and wherein the T-stringer and the omega stringer are applied to the shell component or to edges of the shell component; a connection arrangement, wherein the connecting arrangement connects the T-stringer and the omega stringer in their longitudinal directions, the connection arrangement comprising: at least one foot portion connecting element connected rigidly to the foot portion of the T-stringer and to the foot portion of the omega stringer, wherein the at least one foot portion connecting element is adapted on one end to have a shape corresponding to a geometric shape of the foot portion of the T-stringer and is adapted on another end to have a shape corresponding to a geometric shape of the foot portion of the omega stringer; and two comb portion connecting elements each connected rigidly to the comb portion of the T-stringer and to the comb portion of the omega stringer, wherein the two comb portion connecting elements are each adapted on one end to have a shape corresponding to a geometric shape of the comb portion of the T-stringer and are each adapted on another end to have a shape corresponding to a geometric shape of the comb portion of the omega stringer; wherein a center axis of the T-stringer is laterally offset with respect to a center axis of the omega stringer, and wherein one of the two comb portion connecting elements is moved upwards or downwards with respect to the other of the two comb portion connecting elements on an oblique outer surface of the omega stringer in order to compensate for the offset.