| 摘要 |
<p>The invention relates to a structural component for an aircraft or spacecraft, comprising an external skin (102) and a first stiffening element (104) which extends along a first direction (112) in space on the external skin. A second stiffening element (110) extends in a second direction (114) in space above the first stiffening element. A base element (108) supports the second stiffening element on the external skin. The base element has a through-hole (116) within which the first stiffening element is positively retained. The invention also relates to a method for stiffening an external skin of an aircraft or spacecraft. In said method, a first stiffening element is mounted on the external skin along a first direction in space. A base element that has a through-hole is mounted above the first stiffening element in such a way that the first stiffening element is positively retained within the through-hole. A second stiffening element is mounted on the base element above the first stiffening element in a second direction in space.</p> |
