Performance of an auxetic honeycomb-core sandwich panel under close-in and far-field detonations of high explosive

2021 ◽  
pp. 114907
Author(s):  
Rajendra Prasad Bohara ◽  
Steven Linforth ◽  
Abdallah Ghazlan ◽  
Tuan Nguyen ◽  
Alex Remennikov ◽  
...  
Keyword(s):  
Sandwich Panel ◽  
High Explosive ◽  
Far Field ◽  
Honeycomb Core

Numerical modeling of high velocity impact in sandwich panels with honeycomb core and composite skin including composite progressive damage model

2018 ◽  
Vol 22 (8) ◽  
pp. 2768-2795 ◽  
Author(s):  
Meysam Khodaei ◽  
Mojtaba Haghighi-Yazdi ◽  
Majid Safarabadi
Keyword(s):  
Numerical Model ◽  
Sandwich Panel ◽  
Material Model ◽  
Absorption Capacity ◽  
Numerical Results ◽  
Ballistic Impact ◽  
Experimental Results ◽  
Ballistic Limit ◽  
Honeycomb Core ◽  
Damage Initiation

In this paper, a numerical model is developed to simulate the ballistic impact of a projectile on a sandwich panel with honeycomb core and composite skin. To this end, a suitable material model for the aluminum honeycomb core is used taking the strain-rate dependent properties into account. To validate the ballistic impact of the projectile on the honeycomb core, numerical results are compared with the experimental results available in literature and ballistic limit velocities are predicted with good accuracy. Moreover, to achieve composite skin material model, a VUMAT subroutine including damage initiation based on Hashin’s seven failure criteria and damage evolution based on MLT approach modulus degradation is used. To validate the composite material model VUMAT subroutine, the ballistic limit velocities of the projectile impact on the composite laminates are predicted similar to the numerical results presented by other researchers. Next, the numerical model of the sandwich panel ballistic impact at different velocities is compared with the available experimental results in literature, and energy absorption capacity of the sandwich panel is predicted accurately. In addition, the numerical model simulated the sandwich panel damage mechanisms in different stages similar to empirical observations. Also, the composite skin damages are investigated based on different criteria damage contours.

Pressure-Impulse Diagrams for Paper Honeycomb Core Sandwich Panel Using Finite Element Method

2021 ◽  
pp. 295-306
Author(s):  
Payal Shirbhate ◽  
Shreya Korde ◽  
Manmohan Dass Goel
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Sandwich Panel ◽  
Honeycomb Core ◽  
Pressure Impulse ◽  
Paper Honeycomb ◽  
Element Method

GS0319 Study on Local Compression Fatigue Property of Honeycomb Core Sandwich Panel Using CFRP for Face Sheet : Influence of Fiber Direction of Face Sheet

2016 ◽  
Vol 2016.22 (0) ◽  
pp. _GS0319-1_-_GS0319-2_
Author(s):  
Yuta HARADA ◽  
Yukiyoshi KOBAYASHI ◽  
Yoshinao KISHIMOTO ◽  
Toshihisa OHTSUKA
Keyword(s):  
Sandwich Panel ◽  
Fatigue Property ◽  
Face Sheet ◽  
Fiber Direction ◽  
Honeycomb Core

Consideration about Local Compression Fatigue Strength of Honeycomb Core Sandwich Panel Using CFRP for Face Sheet

2017 ◽  
Vol 2017 (0) ◽  
pp. G0300804
Author(s):  
Yuta HARADA ◽  
Yukiyoshi KOBAYASHI ◽  
Yoshinao KISHIMOTO ◽  
Toshihisa OHTSHUKA
Keyword(s):  
Fatigue Strength ◽  
Sandwich Panel ◽  
Face Sheet ◽  
Honeycomb Core

scholarly journals Impact Property of Double Layer Honeycomb Core Sandwich Panel

2009 ◽  
Vol 75 (758) ◽  
pp. 1409-1415 ◽  
Author(s):  
Yukiyoshi KOBAYASHI ◽  
Toshihisa OHTSUKA ◽  
Masaya HIRAHARA
Keyword(s):  
Double Layer ◽  
Sandwich Panel ◽  
Impact Property ◽  
Honeycomb Core

Light-weight sandwich panel honeycomb core with hybrid carbon-glass fiber composite skin for electric vehicle application

2016 ◽  
Author(s):  
Sukmaji Indro Cahyono ◽  
Angit Widodo ◽  
Miftahul Anwar ◽  
Kuncoro Diharjo ◽  
Teguh Triyono ◽  
...  
Keyword(s):  
Glass Fiber ◽  
Electric Vehicle ◽  
Sandwich Panel ◽  
Fiber Composite ◽  
Light Weight ◽  
Honeycomb Core ◽  
Glass Fiber Composite ◽  
Hybrid Carbon

Investigation of Core Node Separation and Crush

2010 ◽  
Vol 129-131 ◽  
pp. 164-168
Author(s):  
Fen Yu ◽  
Shi Leonard ◽  
Fei Long Yang
Keyword(s):  
High Pressure ◽  
Sandwich Panel ◽  
Historical Data ◽  
Statistic Analysis ◽  
Honeycomb Core ◽  
Core Node ◽  
Analysis Calculation ◽  
Core Thickness ◽  
Relationship Of ◽  
The Relationship

The causes of the honeycomb core node separation/core crush defects of fiberglass sandwich panel is analyzed. The porosity of skin and leakage of vacuum bag under high-pressure curing environment are identified as root causes based on the analysis of historical data and designed simulation testes, and approved by statistic analysis calculation also. The relationship of core thickness and the opportunity of the defects appearing are discovered by tests.

scholarly journals High Temperature Mechanical Properties of a Vented Ti-6Al-4V Honeycomb Sandwich Panel

Materials ◽  
2020 ◽  
Vol 13 (13) ◽  
pp. 3008
Author(s):  
Lei Shang ◽  
Ye Wu ◽  
Yuchao Fang ◽  
Yao Li
Keyword(s):  
Mechanical Properties ◽  
High Temperature ◽  
Cell Walls ◽  
Sandwich Panel ◽  
Sandwich Panels ◽  
Honeycomb Core ◽  
Compression Performance ◽  
High Temperature Mechanical Properties ◽  
Honeycomb Sandwich ◽  
The Face

For aerospace applications, honeycomb sandwich panels may have small perforations on the cell walls of the honeycomb core to equilibrate the internal core pressure with external gas pressure, which prevent face-sheet/core debonding due to pressure build-up at high temperature. We propose a new form of perforation on the cell walls of honeycomb sandwich panels to reduce the influence of the perforations on the cell walls on the mechanical properties. In this paper, the high temperature mechanical properties of a new vented Ti-6Al-4V honeycomb sandwich panel were investigated. A vented Ti-6AL-4V honeycomb sandwich panel with 35Ti-35Zr-15Cu-15Ni as the filler alloy was manufactured by high-temperature brazing. The element distribution of the brazed joints was examined by means of SEM (scanning electron microscopy) and EDS (energy-dispersive spectroscopy) analyses. Compared to the interaction between the face-sheets and the brazing filler, the diffusion and reaction between the honeycomb core and the brazing filler were stronger. The flatwise compression and flexural mechanical properties of the vented honeycomb sandwich panels were investigated at 20, 160, 300, and 440 °C, respectively. The flatwise compression strength, elastic modulus, and the flexural strength of the vented honeycomb sandwich panels decreased with the increase of temperature. Moreover, the flexural strength of the L-direction sandwich panels was larger than that of the W-direction sandwich panels at the same temperature. More importantly, the vented honeycomb sandwich panels exhibited good compression performance similar to the unvented honeycomb sandwich panels, and the open holes on the cell walls have no negative effect on the compression performance of the honeycomb sandwich panels in these conditions. The damage morphology observed by SEM revealed that the face-sheets and the brazing zone show ductile and brittle fracture behaviors, respectively.

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