Validation of damage modelling in composite fuselage structures under high velocity impact

• Published in: CEAS aeronautical journal Vol. 4; no. 3; pp. 253 - 264
• Main Authors: Johnson, Alastair F., Toso-Pentecôte, Nathalie, Kilchert, Sebastian
• Format: Journal Article
• Language: English
• Published: Vienna Springer Vienna 2013
• Subjects: Aerospace Technology and Astronautics; Engineering; Original Paper; FE code developments; Foldcore sandwich panels; Certification by analysis; Stiffened aircraft panels; Simulation of impact damage; Composite damage; Delamination models
• ISSN: 1869-5582; 1869-5590
• DOI: 10.1007/s13272-013-0071-2

The paper discusses finite element (FE) simulation methods in use for predicting impact damage in advanced composite structures. Before these simulation tools are accepted by the industry for design and certification of composite aircraft structures, composites damage models have to be developed, implemented in commercial FE codes and validation studies at specimen and substructure level have to be performed. For vulnerability analysis, the DLR uses meso-scale composites ply damage models with an energy-based delamination failure criteria in explicit FE codes to study damage progression in composite structures under impact. The methods developed are summarised in the paper and applied to predict impact damage in stiffened aircraft panels and novel foldcore sandwich structures from hard debris. Issues concerned with use of such computational methods for certification by analysis are discussed.