Discrete modelling of low-velocity impact on Nomex® honeycomb sandwich structures with CFRP skins. (1st January 2019)

• Record Type: Journal Article
• Authors: Audibert, Clément; Andréani, Anne-Sophie; Lainé, Éric; Grandidier, Jean-Claude
• Is Part Of: Composite structures. Volume 207(2019)
• Page Start: 108
• Page End: 118
• Publication Date: 2019-01-01
• Subjects: Honeycomb -- Impact behavior -- Computational modelling -- Mechanical testing; Composite construction -- Periodicals; Composites -- Périodiques; 624.18
• DOI: 10.1016/j.compstruct.2018.09.047
• Languages: English
• ISSNs: 0263-8223

Abstract

Abstract: Predicting the honeycomb sandwich's response to impact loading is a major challenge in the aeronautical industry. Several papers demonstrated the possible use of non-linear springs to model Nomex's impact behavior. On the other hand, the authors show that the lack of transverse shear consideration constitutes a real limitation. The aim of this study is to overcome this limitation by introducing a compression/shear coupling to take into account the transverse shear. In this approach, the modelling of a low velocity impact test is performed on a sandwich composite with CFRP skins and Nomex® honeycomb. Composite skins are modeled as an elasto-plastic-damage material using a user field surbroutine (Abaqus©). The Nomex core is modeled with non-linear springs integrating a compression/shear coupling behavior. Then, the sandwich response under low speed impact is realized and compared with experimental data leading to a good correlation.