| 摘要 |
A structural component such as wing skin (1) for an aircraft is formed generally of a first composite fibre and matrix material exhibiting a first tensile modulus in respect of tensile stress and a first tolerance of strain resulting from such stress. One or more openings (5, 6, 7) are provided in t he component and the material of a portion of the component bounding the opening(s) is a second composite fibre and matrix material. The second material exhibits a second tensile modulus in respect of tensile stress that is smaller than the first tensile modulus of the first material and a second tolerance of strain resulting from such stress that is greater than the firs t tolerance of strain of the first material. |
