| 摘要 |
<p>Disclosed is a connecting arrangement for joining two stiffening elements (1, 2) of an aircraft or spacecraft. The stiffening elements (1, 2) have different cross-sectional profiles with at least one base section (3, 4) and at least one rib section (5, 6). In said connecting arrangement, at least one base section connecting element (7, 7') can be adapted to the geometrical shape of the base section (3) of the first stiffening element (1) on one side and to the geometrical shape of the base section (4) of the second stiffening element (2) on the opposite side and can be fixedly connected thereto. Furthermore, at least one rib section connecting element (8, 8') can be adapted to the geometrical shape of the rib section (5) of the first stiffening element (1) on one side and to the geometrical shape of the rib section (6) of the second stiffening element (2) on the opposite side and can be fixedly connected thereto. A shell component comprising at least two stiffening elements (1, 2) that have different cross-sectional profiles is equipped with said connecting arrangement.</p> |
