Shock loading response of sandwich panels with 3-D woven E-glass composite skins and stitched foam core

2009 ◽  
Vol 69 (6) ◽  
pp. 736-753 ◽  
Author(s):  
Srinivasan Arjun Tekalur ◽  
Alexander E. Bogdanovich ◽  
Arun Shukla
Keyword(s):  
Shock Loading ◽  
Sandwich Panels ◽  
Foam Core ◽  
Glass Composite ◽  
Composite Skins

Investigation of progressive failure in the composite sandwich panels with elastomeric foam core under concentrated loading

2017 ◽  
Vol 21 (8) ◽  
pp. 2585-2615
Author(s):  
AR Nazari ◽  
MZ Kabir ◽  
H Hosseini-Toudeshky ◽  
Y Alizadeh Vaghasloo ◽  
S Najafian
Keyword(s):  
Energy Absorption ◽  
Composite Laminates ◽  
Sandwich Panels ◽  
Absorption Capacity ◽  
Foam Core ◽  
Energy Absorption Capacity ◽  
Composite Sandwich Panels ◽  
Composite Sandwich ◽  
Load Carrying ◽  
Composite Skins

Failure and damage of crushable materials employed as core for the sandwich structures reduces serviceability and energy absorption capacity of the components especially under bending load so that many beneficial properties seem to be achieved by application of noncrushable lightweight materials instead of crushable foams as core for the sandwich structures. In this paper, an elastomeric foam is employed as core for two aspect ratios of the composite sandwich panels and the enhancement of the load-carrying capacity in the elastomeric foam-cored sandwich panels is investigated in comparison to which is measured about the individual composite panels applied as skins. Both experimental and finite element simulation programs are included in the research. The load-carrying performance of the elastomeric foam-cored sandwich panels is considered dependent on two main features of the constituent materials as hyperelastic behavior of the foam core and progressive damage of the composite skins which are simulated in the finite element models in order to describe the failure mechanism in the panels. Collapse of the elastomeric foam-cored sandwich panels is considered due to connection of some failure lines in the composite skins; however, the foam core remains undamaged. The elastomeric foam core can transfer the load from the top composite skin to the bottom one so that a great energy absorption capacity is provided for these panels. The elastomeric foam after failure of the composite skins can mobilize the residual strength of the laminates to endure against large deformations prior to final collapse. By application of the composite laminates in sandwich form with elastomeric foam core, the maximum load carrying and energy absorption capacity of the composite laminates increased about 60 and 110%, respectively. The results show more favorite failure behavior for the elastomeric foam-cored sandwich panels in comparison to which is expected usually for the crushable foam-cored sandwich panels which may be concerned in many industrial applications.

Closure to “Local Failure of Plastic-Foam Core Sandwich Panels”

1970 ◽  
Vol 96 (8) ◽  
pp. 1803-1805
Author(s):  
Billy J. Harris ◽  
Gene M. Nordby
Keyword(s):  
Sandwich Panels ◽  
Local Failure ◽  
Foam Core ◽  
Plastic Foam

Local Failure of Plastic-Foam Core Sandwich Panels

1969 ◽  
Vol 95 (4) ◽  
pp. 585-610
Author(s):  
Billy J. Harris ◽  
Gene M. Nordby
Keyword(s):  
Sandwich Panels ◽  
Local Failure ◽  
Foam Core ◽  
Plastic Foam

scholarly journals Thermal-mechanical behavior of sandwich panels with closed-cell foam core under intensive laser irradiation

2014 ◽  
Vol 18 (5) ◽  
pp. 1607-1611 ◽  
Author(s):  
Zhi-Qiang Li ◽  
Wei-Dong Song ◽  
Hui-Ping Tang ◽  
Zhi-Hua Wang ◽  
Long-Mao Zhao
Keyword(s):  
Thermal Conductivity ◽  
Thermal Stress ◽  
Specific Heat ◽  
Laser Irradiation ◽  
Thermal Deformation ◽  
Sandwich Panels ◽  
Protective Layer ◽  
Foam Core ◽  
Closed Cell ◽  
Analysis Models

Temperature field and thermal deformation of sandwich panels with closed-cell aluminum alloy foam core and heat-protective layer, which are subjected to Gaussian laser beam intensively irradiating, are investigated numerically. In transient heat analysis models, the influence of thermal conductivity, specific heat, and thickness of heat-protective layer on the temperature rise of the sandwich panels is calculated. In stress analysis models, a sequence coupled numerical method is utilized to simulate the thermal stress and deformation of sandwich panels induced by thermal expansion. Simulation results indicate that the temperature at center of sandwich panel increases firstly and then drops gradually with the increase of thermal conductivity of heat-protective layer after laser irradiation, and the critical thermal conductivity is obtained, while it decreases with the increase of specific heat and thickness of heat-protective layer. The thermal stress verifies the ?Cyclo-hoop effect?, i. e. radial stress is compression stress in ?hot zone? and tension stress in ?cold zone?. The max thermal deformation of sandwich panels slightly increases with the increase of thickness of heat-protective layer for given specific heat and thermal conductivity.

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