A Computational Study on Residual Strength of Sandwich Composite Panel

2011 ◽  
Vol 393-395 ◽  
pp. 521-525 ◽  
Author(s):  
Sang Kyo Lee ◽  
Mohd. Zahid Ansari ◽  
Na Wang ◽  
Chong Du Cho
Keyword(s):  
Residual Strength ◽  
Computational Study ◽  
Static Condition ◽  
Composite Panel ◽  
Sandwich Composite ◽  
Element Analysis ◽  
Reinforced Plastic ◽  
Out Of Plane ◽  
Aluminum Honeycomb ◽  
Plane Direction

The present study investigates numerically the compressive residual strength of indented sandwich composite panel. The composite is made of carbon fiber reinforced plastic (CFRP) face sheets and aluminum honeycomb core. The sandwich is loaded under quasi-static condition and along out-of-plane direction. A commercial finite element analysis software ABAQUS is used. The results show that the indented composite retains significant amount of strength after indentation. And, the post-indentation strength of the composite is about 65% its pre-indentation strength under compression.

Experimental and Finite Element Based Investigations of In-Plane and Out-of-Plane Properties of Aluminum Honeycomb

2013 ◽  
Vol 275-277 ◽  
pp. 111-116 ◽  
Author(s):  
Muhammad Kashif Khan ◽  
Qing Yuan Wang
Keyword(s):  
Finite Element ◽  
Sample Size ◽  
Cell Size ◽  
Mechanical Response ◽  
Honeycomb Core ◽  
Element Analysis ◽  
Out Of Plane ◽  
Aluminum Honeycomb ◽  
Plane Direction ◽  
Honeycomb Cores

Experimental and Finite Element analysis was used for the investigation of the effect of cell size and thickness on the compressive properties of Aluminium honeycomb core. Honeycomb cores were compressed experimentally in in-plane and out of plane directions. The effect of sample size, cell size and thickness on the elastic modulus, yield strength and plateau stress was investigated through FEA. It was found that the mechanical response was independent upon the sample size in in-plane direction. The smallest cell size honeycomb core was deformed at higher yield stress. Similarly, with increase in cell wall thickness, the modulus of the core increased.

Simulation for the Bird-Strike Damage of Drone Radome Composite Structure

2012 ◽  
Vol 151 ◽  
pp. 305-309 ◽  
Author(s):  
Yan Bin He ◽  
Xiao Hu Yao ◽  
Xuan Liu ◽  
Ling Feng He
Keyword(s):  
Composite Structure ◽  
Impact Damage ◽  
Dynamic Responses ◽  
Composite Panel ◽  
Sandwich Composite ◽  
Bird Strike ◽  
Damage State ◽  
Element Analysis ◽  
Medium Speed ◽  
Maximum Impact Force

The low and medium speed bird-strike impact damage of sandwich composite structure of drone radome during takeoff and landing is examined by numerical simulations, using nonlinear dynamic finite element analysis software LS-DYNA. For different impact velocities, the aircraft radome’s dynamic responses are obtained and the damage in composite panel is clearly demonstrated. The relations of impact energy, maximum impact force and the damage state are analyzed. The simulation results can provide some references for the aircraft radome design.

Combined Compression-Shear Behavior of Aluminum Honeycombs

2014 ◽  
Vol 626 ◽  
pp. 127-132 ◽  
Author(s):  
Asm Ashab ◽  
Dong Ruan ◽  
Guo Xing Lu ◽  
Yat C. Wong
Keyword(s):  
Mechanical Response ◽  
Indentation Load ◽  
Shear Loading ◽  
Plane Orientation ◽  
Out Of Plane ◽  
Aluminum Honeycomb ◽  
Good Energy ◽  
Plane Direction ◽  
Crushing Behavior ◽  
Naval Engineering

Aluminum honeycombs are lightweight and have good energy absorption capability. They are widely used in industrial products and also as core materials in various fields of engineering such as aerospace, automotive and naval engineering because of their high specific strengths and they can undergo large plastic deformation to absorb high impact energy. In the applications of aluminum honeycombs they are not only subjected to pure compressive or indentation load but sometime also under combined compression-shear load. The mechanical response and crushing behavior under combined compression-shear loading condition is still limited in literature. In this paper, quasi-static out-of-plane combined compression-shear tests were conducted to study the deformation mechanism of different types of HEXCELL® aluminum honeycombs with different cell sizes and wall thicknesses. Three types of aluminum honeycombs were used in this study. A universal MTS machine with specially designed fixtures was employed in the quasi-static loading tests. The experiments were conducted at three different loading angles, that is, 30°, 45° and 60° and in TL and TW (T is out-of-plane direction and L, W are the two in-plane directions) plane orientation loading directions of aluminum honeycomb. The effects of different loading angle and different plane orientation are reported in this experimental study. Similarly, the effects of cell size and cell wall thickness were also analyzed.

The Damage of Sandwich Composite Structure of Aircraft Radome under Debris-Strike

2011 ◽  
Vol 63-64 ◽  
pp. 515-518 ◽  
Author(s):  
Xiao Qing Zhang ◽  
Xuan Liu
Keyword(s):  
Composite Structure ◽  
Impact Damage ◽  
Dynamic Responses ◽  
Composite Panel ◽  
Sandwich Composite ◽  
Damage State ◽  
Element Analysis ◽  
Medium Speed ◽  
Maximum Impact Force ◽  
Sandwich Composite Structure

The low and medium speed impact damage of sandwich composite structure of aircraft radome shield under debris-strike during takeoff and landing along runway is examined by numerical simulations, using nonlinear dynamic finite element analysis software LS-DYNA. For different impact velocities, the dynamic responses of aircraft radome shield are obtained and the damage in composite panel is clearly demonstrated. The relations of impact energy, maximum impact force and the damage state are analyzed. The simulation results can provide some references for the design of aircraft radome.

An Experimental and Computational Study on the Low Velocity Impact-induced Damage of a Highly Anisotropic Laminated Composite Panel

2021 ◽  
pp. 1-31
Author(s):  
Shiyao Lin ◽  
Anthony Waas
Keyword(s):  
Computational Models ◽  
Computational Study ◽  
Laminated Composite ◽  
Model Material ◽  
Low Velocity Impact ◽  
Composite Panel ◽  
Sandwich Composite ◽  
Cohesive Law ◽  
Low Velocity ◽  
Velocity Impact

Abstract The low velocity impact (LVI) induced damage of a highly anisotropic laminate [0/90/0/90\textsubscript{9}]\textsubscript{s} has been studied experimentally and numerically. The purpose of the analyses of this laminate is that this stacking sequence resembles a sandwich composite panel, in the sense that the [0/90/0] outer layers serve as the “face sheet” while the inner 18 plies of 90° layers serve as the “core”. The LVI induced damage pattern of this laminate is unique and referred to as the “kidney” shape. The “kidney” shape damage is caused by a strong interaction between matrix transverse cracking and delamination, hence is challenging to be computationally captured. The Enhanced Schapery Theory (EST) model has been improved with the capability to model material inelasticity, as well as a novel mixed-mode cohesive law, to tackle this problem. EST with inelasticity (EST-InELA) is shown to be able to predict load responses and damage morphology accurately and efficiently. The aim of this paper is to provide a benchmark LVI case to challenge and calibrate computational models.

A Study on the Bending Analysis of the Al Honeycomb Core Sandwich Composite Panel Bearing Large Bending Load

2013 ◽  
Vol 702 ◽  
pp. 245-252 ◽  
Author(s):  
Hong Gun Kim ◽  
Young Jun Kim ◽  
Hee Jae Shin ◽  
Sun Ho Ko ◽  
Hyun Woo Kim ◽  
...  
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Tensile Modulus ◽  
Composite Panel ◽  
Sandwich Composite ◽  
Test Results ◽  
Honeycomb Core ◽  
Element Analysis ◽  
Bending Load ◽  
The Finite Element Analysis

Al honeycomb core sandwich composite panels have different core and plate materials. The core is the Al honeycomb core, and the thin plate is GFRP sheets with fibers laminated in the 0°/90° symmetric structure. The Al honeycomb core sandwich composite panel is used for structures, which involve relatively high bending load. Before designing the structures, their stability is evaluated via the finite element analysis. In this study, an analysis method that is closest to the reality was proposed for designing the structures with Al honeycomb core sandwich composite panels. For that purpose, the modulus was reviewed. In the finite element analysis, the tensile modulus is generally used. In the results of this study, however, the tensile modulus led to significant deviations from the test results, whereas the bending modulus led to a closer value to the test results.

scholarly journals Characterization and ballistic performance of thin pre-damaged resin-starved aramid-fiber composite panels

2021 ◽  
pp. 004051752110134
Author(s):  
Cerise A Edwards ◽  
Stephen L Ogin ◽  
David A Jesson ◽  
Matthew Oldfield ◽  
Rebecca L Livesey ◽  
...  
Keyword(s):  
Fiber Composite ◽  
Plane Deformation ◽  
Ballistic Impact ◽  
Image Correlation ◽  
Composite Panel ◽  
Composite Panels ◽  
Micro Computed Tomography ◽  
Ballistic Performance ◽  
Low Level ◽  
Out Of Plane

Military personnel use protective armor systems that are frequently exposed to low-level damage, such as non-ballistic impact, wear-and-tear from everyday use, and damage during storage of equipment. The extent to which such low-level pre-damage could affect the performance of an armor system is unknown. In this work, low-level pre-damage has been introduced into a Kevlar/phenolic resin-starved composite panel using tensile loading. The tensile stress–strain behavior of this eight-layer material has been investigated and has been found to have two distinct regions; these have been understood in terms of the microstructure and damage within the composite panels investigated using micro-computed tomography and digital image correlation. Ballistic testing carried out on pristine (control) and pre-damaged panels did not indicate any difference in the V50 ballistic performance. However, an indication of a difference in response to ballistic impact was observed; the area of maximal local out-of-plane deformation for the pre-damaged panels was found to be twice that of the control panels, and the global out-of-plane deformation across the panel was also larger.

scholarly journals Locally Corroded Stiffener Effect on Shear Buckling Behaviors of Web Panel in the Plate Girder

2015 ◽  
Vol 2015 ◽  
pp. 1-19 ◽  
Author(s):  
Jungwon Huh ◽  
In-Tae Kim ◽  
Jin-Hee Ahn
Keyword(s):  
Corrosion Damage ◽  
Element Analysis ◽  
Buckling Strength ◽  
Lower Shear ◽  
Out Of Plane ◽  
Shear Buckling ◽  
Buckling Failure ◽  
Plane Displacement ◽  
The Web ◽  
Plate Girder

The shear buckling failure and strength of a web panel stiffened by stiffeners with corrosion damage were examined according to the degree of corrosion of the stiffeners, using the finite element analysis method. For this purpose, a plate girder with a four-panel web girder stiffened by vertical and longitudinal stiffeners was selected, and its deformable behaviors and the principal stress distribution of the web panel at the shear buckling strength of the web were compared after their post-shear buckling behaviors, as well as their out-of-plane displacement, to evaluate the effect of the stiffener in the web panel on the shear buckling failure. Their critical shear buckling load and shear buckling strength were also examined. The FE analyses showed that their typical shear buckling failures were affected by the structural relationship between the web panel and each stiffener in the plate girder, to resist shear buckling of the web panel. Their critical shear buckling loads decreased from 82% to 59%, and their shear buckling strength decreased from 88% to 76%, due to the effect of corrosion of the stiffeners on their shear buckling behavior. Thus, especially in cases with over 40% corrosion damage of the vertical stiffener, they can have lower shear buckling strength than their design level.

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