Modelling of bird strike on an aircraft wing leading edge made from fibre metal laminates - Part 1: Material modelling
Modelling of bird strike on an aircraft wing leading edge made from fibre metal laminates - Part 1: Material modelling
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DOI：
10.1023/b:acma.0000037133.64496.13
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发表时间：
2004-09-01
影响因子：
2.3
通讯作者：
Melito, V
中科院分区：
文献类型：
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作者：
McCarthy, MA;Xiao, JR;Melito, V
据报道，具有多层铝合金和高强度玻璃纤维复合材料的纤维金属层合板具有优异的冲击性能，适用于可能受到跑道碎片或鸟类等物体冲击的飞机部件。在一个合作研究项目中，设计、制造了具有玻璃基FML蒙皮的飞机机翼前缘结构，并进行了鸟撞试验，并用有限元分析对其进行了建模。在这篇由两部分组成的论文的第一部分中，提出了一种适合于采用显式有限元分析进行碰撞建模的FML材料模型。该材料模型基于商业有限元程序PAM-CRASH/SHOCK中的复合材料连续损伤力学(CDM)模型的最新实现，考虑了各向异性应变率效应。将该模型的结果与FML在不同应变率下的实验结果进行了比较，结果表明该模型能够捕捉到这些材料表现出的大部分复杂的应变率依赖行为。
Fibre Metal Laminates with layers of aluminium alloy and high strength glass fibre composite have been reported to possess excellent impact properties and be suitable for aircraft parts likely to be subjected to impacts from objects such as runway debris or birds. In a collaborative research project, aircraft wing leading edge structures with a glass-based FML skin have been designed, built, and subjected to bird strike tests that have been modelled with finite element analysis. In this first part of a two-part paper, a material model developed for FML suitable for use in impact modelling with explicit finite element analysis is presented. The material model is based on a recent implementation in the commercial finite element code PAM-CRASH/SHOCK of a Continuum Damage Mechanics (CDM) model for composites, incorporating anisotropic strain rate effects. Results from the model are compared with experimental results on FML at variable strain rates and the model is shown to be capable of capturing most of the complex strain rate dependent behaviour exhibited by these materials.