Simulation of High Velocity Impact on Composite Structures - Model Implementation and Validation
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Simulation of High Velocity Impact on Composite Structures - Model Implementation and Validation Dominik Schueler 1 & Nathalie Toso-Pentecôte 1 & Heinz Voggenreiter 1
Received: 30 March 2016 / Accepted: 4 April 2016 # Springer Science+Business Media Dordrecht 2016
Abstract 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 Ladevèze 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. Keywords Composite damage . Delamination . High velocity impact . Non-destructive evaluation . FE simulation of impact
1 Introduction Composite aircraft structures such as fuselage or wing skins are vulnerable to impact damage resulting from impacting hard or soft bodies like runway debris or birds. The objective of the present work is to develop a numerical simulation methodology to simulate such impact events offering a sizing tool and cost savings through a reduction in development time in an industrial context [1]. In the paper the term high velocity impact (HVI) is defined as impact resulting in flexural waves that govern the target response [2].
* Dominik Schueler [email protected]
1
German Aerospace Center (DLR), Institute of Structures and Design, Pfaffenwaldring 38-40, 70569 Stuttgart, Germany
Appl Compos Mater
Impact on composite structures results in complex failure mechanisms including delamination and various intra-ply damage modes. Ladevèze and co-workers [3, 4] developed a mesoscale model in which the laminate is represented by the two basic constituents: ply and interface. The term ‘mesoscale’ indicates that the micromechanical behaviour including damage evolution and crack propagation is homogenized such that the micro effects of material degradation are captured on a higher ‘meso’-level within the ply and interface models. Here the mesoscale approach is simplified further for the simulation on element and component level by modelling the laminate with layers of shell elements where each layer represents several plies (sub-laminate). Shell layers are connected by cohesive elements to simulate delamination. This ‘stacked shell approach’ has been implemented into commercial code by Johnson et al. [5] and has been utilized by several other authors [6, 7]. The current
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