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Experience with the finite element modelling of a full-scale test of a composite aircraft control surface

机译:具有复合材料飞机操纵面全面测试的有限元建模经验

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摘要

A full-scale, co-cured, carbon fibre composite control surface representative of those found on mid-size, jet transport aircraft has been designed and tested. It was designed as a postbuckling blade-stiffened structure to reduce weight and improve operational performance compared with a honeycomb sandwich panel design traditionally used in such structures. The purpose of the tests was to demonstrate the validity of the design methodology by applying static limit and ultimate loads to the structure.
机译:已经设计并测试了代表中型喷气运输机上发现的全尺寸,共固化的碳纤维复合材料控制面。与传统上用于此类结构的蜂窝夹芯板设计相比,它被设计为后屈曲叶片加劲肋结构,以减轻重量并提高操作性能。测试的目的是通过对结构施加静态极限和极限载荷来证明设计方法的有效性。

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