By Richard Smith
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Extra info for Arado Ar 234 A (Military Aircraft in Detail)
Survey of failure and post-failure theories of laminated fiber-reinforced composites. J. Compos. Tech. Res. : On the behaviour of composite laminates after initial failures. Astronaut. Aeronaut. : Three-dimensional progressive damage analysis in composite joints.
The monitoring of the progressive failure in each ply of each element during the loading process has been carried out. 3. 20a, b, respectively. For both the load steps only the damage in upper sub-laminate is shown. 20a). This behaviour can be associated to the high compressive stresses perpendicularly to the load direction at the delamination front. A. Riccio et al. 20b) in the delaminated area are failed (fiber + matrix failure mode) due to the increase of compressive stress at the growing delamination front and due to the tensile stress at the center of the panel.
1 The non-linear buckling analysis has been performed on the selected stiffened panel configuration in order to investigate the structural response of the panel itself when subjected to an incremental compressive load up to the global bucking event. The panel, loaded by means of applied displacements, experiences the delamination buckling, the delamination growth and the buckling of the skin. 36 the non-linear deformed shapes with out-of-plane displacements contour plot for the analysed stiffened panel obtained at delamination buckling, delamination growth initiation and global skin buckling are presented.
Arado Ar 234 A (Military Aircraft in Detail) by Richard Smith