Off-campus WSU users: To download campus access dissertations, please use the following link to log into our proxy server with your WSU access ID and password, then click the "Off-campus Download" button below. Non-WSU users: Please talk to your librarian about requesting this thesis through interlibrary loan. Flexural analysis of balsa core sandwich composite: failure mechanisms, core grain orientation and padding effect. Avinash S. Phadatare , Wayne State University Follow.
Buckling and delamination of sandwich structure systems | Research groups | Imperial College London
PQDT Open is getting a new home! Please refer to this FAQ. Composite sandwich plates are widely used in aerospace, automobile and shipbuilding industries. Composite sandwich plates have many different types of failure modes. A comparative study of composite sandwich plates with different finite element modeling approaches for predicting buckling and wrinkling failure response is described in this thesis. The research considers composite sandwich plates with isotropic and anisotropic face-sheets with a thick core. This study investigates results obtained using finite element methods and compares them to experimental and analytical solutions for overall buckling and face-sheet wrinkling.
The sandwich composites fuselages appear to be a promising choice for the future aircrafts because of their structural efficiency and functional integration advantages. However, the design of sandwich composites is more complex than other structures because of many involved variables. In this paper, the fuselage is designed as a sandwich composites cylinder, and its structural optimization using the finite element method FEM is outlined to obtain the minimum weight. The constraints include structural stability and the composites failure criteria. In order to get a verification baseline for the FEM analysis, the stability of sandwich structures is studied and the optimal design is performed based on the analytical formulae.
Sandwich construction is a mass efficient structural form used extensively in astronautic, aeronautic and marine applications. Sandwich panels are used as members for general loading situations: bending, shear and axial loading. In axial compression, however, there are serious structural integrity issues precisely because of their inherent efficiency; their susceptibility to highly unstable interactive buckling phenomena in practical situations is widely accepted . Research conducted by the Nonlinear Mechanics group initially at Imperial College London, then at the University of Bath and again at Imperial has led to the development of a sequence of models that account for the severe interaction between overall Euler-type and local modes of buckling that leads to highly unstable post-buckling [2,3]. Moreover, the practically important issue of buckle pattern localization  has been addressed such that the models can be compared favourably with physical experiments  in a variety of cases.