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Deformation and failure behavior of pre-damaged foam-core sandwich structures in a four-point bending configuration

: John, M.; Schlimper, R.; Mudra, C.

European Society for Composite Materials:
17th European Conference on Composite Materials, ECCM 2016. Proceedings : 26-30th June 2016, Munich, Germany, CD-ROM
Munich, 2016
ISBN: 978-3-00-053387-7
European Conference on Composite Materials (ECCM) <17, 2016, Munich>
Fraunhofer IMWS ()

This article deals with the investigation of the mechanical behavior of predamaged foam-core sandwich structures. A four-point bending fixture was used to investigate the influence of application-specific loads on a sandwich structure with low velocity-impact damage. A typical sandwich failure mode is the occurrence of damages in the skin, the core and in the interface between both, caused by an impact. Impact damaged aircraft structures have to demonstrate sufficient level of damage tolerance and finally residual strength to endure typical damage scenarios without structural failure below the required load level. Currently, for predamaged sandwich structures there is no standardized test available to evaluate deformation behavior and certain residual strength. The main point in this investigation is to develop a significant test setup for a foam-core sandwich structure to observe the deformation and residual strength behavior after a low velocity impact occurred. Finite Element computations were made prior to the test to support specimen design that will show valid failure mode in the compression loaded skin area between the inner force stamps. Predicted specimen internal loads and deformation were reflected by the tests. An applicable specimen dimension and four-point bending test scheme could be proposed for testing of impact damaged foam-core sandwich elements.