期刊
APPLIED COMPOSITE MATERIALS
卷 23, 期 4, 页码 857-878出版社
SPRINGER
DOI: 10.1007/s10443-016-9489-0
关键词
Composite damage; Delamination; High velocity impact; Non-destructive evaluation; FE simulation of impact
资金
- European Community [213371]
High velocity impact on composite aircraft structures leads to the formation of flexural waves that can cause severe damage to the structure. Damage and failure can occur within the plies and/or in the resin rich interface layers between adjacent plies. In the present paper a modelling methodology is documented that captures intra- and inter-laminar damage and their interrelations by use of shell element layers representing sub-laminates that are connected with cohesive interface layers to simulate delamination. This approach allows the simulation of large structures while still capturing the governing damage mechanisms and their interactions. The paper describes numerical algorithms for the implementation of a LadevSze continuum damage model for the ply and methods to derive input parameters for the cohesive zone model. By comparison with experimental results from gas gun impact tests the potential and limitations of the modelling approach are discussed.
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