Nonlinear Behavior of Sandwich Panels with a Transversely Flexible Core

AIAA Journal ◽  
10.2514/2.625 ◽  
1999 ◽  
Vol 37 (11) ◽  
pp. 1474-1482 ◽  
Author(s):  
V. Sokolinsky ◽  
Y. Frostig
Keyword(s):  
Sandwich Panels ◽  
Nonlinear Behavior ◽  
Flexible Core

Nonlinear behavior of sandwich panels with a transversely flexible core

AIAA Journal ◽  
1999 ◽  
Vol 37 ◽  
pp. 1474-1482 ◽  
Author(s):  
V. Sokolinsky ◽  
Y. Frostig
Keyword(s):  
Sandwich Panels ◽  
Nonlinear Behavior ◽  
Flexible Core

Dynamic Response of Sandwich Panels With a Flexible Core Under Simultaneous Low-Velocity Impacts of Multiple Small Masses

2006 ◽  
Author(s):  
K. Malekzadeh ◽  
M. R. Khalili
Keyword(s):  
Dynamic Response ◽  
Plate Theory ◽  
Sandwich Panels ◽  
Shear Deformation Theory ◽  
Core Layer ◽  
Contact Forces ◽  
Low Velocity ◽  
The Face ◽  
The Impact ◽  
Flexible Core

Dynamic response of sandwich panels with a flexible core under simultaneous low-velocity impacts of multiple small masses has investigated in this paper. The contact forces between the panel and the impactors are treated as the internal forces of the system. Shear deformation theory is used for the face sheets while three dimensional elasticity is used for the soft core. The fully dynamic effects of the core layer and the face-sheets are considered in this study. The results in multiple mass impacts over sandwich panels are presented based on proposed improved higher-order sandwich plate theory (IHSAPT). As no literature could be found on the impact of multiple impactors over sandwich panels, the present formulation is validated indirectly by comparing the response of two cases of double small masses and single small mass impacts based on Olsson’s wave control principle.

Buckling of Debonded (Delaminated) Sandwich Panels With Transversely Flexible Core

1999 ◽  
Author(s):  
Y. Frostig ◽  
V. Sokolinsky
Keyword(s):  
Critical Loads ◽  
Sandwich Panel ◽  
Sandwich Panels ◽  
Buckling Analysis ◽  
Face Sheet ◽  
Buckling Modes ◽  
Buckling Behavior ◽  
Edge Delamination ◽  
Flexible Core ◽  
Delamination Length

Abstract Buckling behavior of sandwich panels with a compressible core which are debonded at one of their face sheet-core interfaces is presented. The buckling analysis is based on the principles of the High-Order Sandwich Panel Theory (HSAPT). The effect of the delamination length and location on the critical loads and the buckling modes is studied numerically. Edge delamination as well as inner delamination results are presented. The effect of contact on the critical loads and the buckling modes is presented. A comparison with experimental buckling modes is discussed and conclusions are drawn.

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