| 摘要 |
The invention relates to a composite structural member with fiber reinforcement and its application in the production of a wing box for aircraft. More specifically, it relates to a composite structural member (230) with fiber reinforcement comprising a plurality of layers oriented relative to a longitudinal direction (2) of said member in directions including 0°, 90° and +/−&thetas;, the relative proportion of layers in one of these orientations being variable along a transverse direction (3) of said member so as to spatially adjust the rigidity of the member according to a defined distribution of mechanical stresses along this transverse axis (3). Thus the rigidity of the member is adapted locally to the stress system so as to dissipate the force flux over the entire volume of said member.
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