| 摘要 |
The invention relates to an interior doubling plate 1a for the wall of a fuselage, especially of an aircraft, having a substantially cylindrical shape, and is characterised in that the said plate 1a has rigidity or tensile strength in the circumferential direction which is less than the rigidity or tensile strength in the longitudinal direction. This is brought about either by making the plate include folds in the longitudinal direction, or, in the case in which the plate is made of fibre-reinforced plastic, by arranging the fibres along specific orientations with respect to the longitudinal direction of the fuselage. <IMAGE>
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