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Modelling of impact damage zones in composite laminates for strength after impact
RISE, Swerea, SICOMP.ORCID iD: 0000-0002-2627-3280
2012 (English)In: Aeronautical Journal, ISSN 0001-9240, Vol. 116, no 1186, p. 1349-1365Article in journal (Refereed) Published
Abstract [en]

This paper reviews findings on the type, morphology and constitutive behaviour of impact damage zones during loading after impact and their effect on the laminate strength and stability. The paper is limited to tape prepreg based monolithic laminates, although some similarities exist with impact damage in textile based laminates. Damage zones have a complex geometry with several damage types, which results in an interaction and competition between different failure mechanisms, e.g. local and global buckling, compressive failure, and delamination growth. Hence, simplified damage models may provide incorrect predictions of the failure load and failure mechanisms after impact. The constitutive behaviour of damage zones has been studied experimentally in tension and compression using an inverse method, and the results have been compared with detailed FE models of a generic impact damage. The paper is concluded with a discussion on analytical and computational models to predict the resulting strength of impacted laminates.

Place, publisher, year, edition, pages
Royal Aeronautical Society , 2012. Vol. 116, no 1186, p. 1349-1365
Keywords [en]
Buckling, Failure (mechanical), Inverse problems, Laminated composites, Paper laminates, Complex geometries, Composite laminate, Compressive failure, Computational model, Constitutive behaviour, Delamination growth, Simplified damage models, Tension and compression, Laminates
National Category
Natural Sciences
Identifiers
URN: urn:nbn:se:ri:diva-40972DOI: 10.1017/S0001924000007673Scopus ID: 2-s2.0-84872331506OAI: oai:DiVA.org:ri-40972DiVA, id: diva2:1376971
Available from: 2019-12-10 Created: 2019-12-10 Last updated: 2019-12-10Bibliographically approved

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Olsson, Robin

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