In-plane compression of sandwich panels with debonds
2010 (English)In: Composite structures, ISSN 0263-8223, E-ISSN 1879-1085, Vol. 92, no 2, 532-540 p.Article in journal (Refereed) Published
The post failure behaviour of in-plane compression loaded sandwich panels is studied by considering the structural response of such panels with symmetrically located edge debonds. A parametric finite element model is used to determine the influence of different material and geometrical properties on the failure progression, i.e. after initiation of damage. The investigated failure modes are buckling of the debonded face sheets, debond propagation and face sheet failure. The postbuckling failure mode is mainly determined by the fracture toughness of the core and the bending stiffness and strength of the face sheets. The presented approach and results can be used to determine how sandwich panels should be constituted, or not, to promote damage progression favourable for efficient energy absorption during in-plane crushing. The prolonged damage propagation is very complex as it is strongly non-linear and depends on a combination of stiffness, strength and geometry of the constituent materials.
Place, publisher, year, edition, pages
Oxford, UK: Elsevier , 2010. Vol. 92, no 2, 532-540 p.
Sandwich; Fracture; Finite element analysis (FEA)
Composite Science and Engineering
IdentifiersURN: urn:nbn:se:kth:diva-11155DOI: 10.1016/j.compstruct.2009.08.039ISI: 000271561100038ScopusID: 2-s2.0-70349801487OAI: oai:DiVA.org:kth-11155DiVA: diva2:236435
QC 201007282009-09-232009-09-232016-05-16Bibliographically approved