| 摘要 |
The invention relates to an integrated structure of a composite material multispar torsion box (1) for aircraft, comprising a lower skin (12), an upp er skin (11), several spars (9) defining cells (14), the first cell (19) bei ng the closest to the input of load in the box (1), said structure comprisin g unit elements in the first cell, which unit elements provide the torsion b ox (1) with the necessary torsional rigidity to prevent the deformations occ urring as a result of local loads.
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