scholarly journals Analysis of effect of variation of Honeycomb core cell size and sandwich panel width on the stiffness of a sandwich structure

2022 ◽  
Author(s):  
Anil Kumar ◽  
◽  
Surjit Angra ◽  
Arindam Kumar Chanda ◽  
◽  
...  
Keyword(s):  
Cell Size ◽  
Sandwich Structure ◽  
Sandwich Panel ◽  
Composite Panel ◽  
Design Parameters ◽  
Equivalent Stiffness ◽  
Honeycomb Core ◽  
Composite Sandwich ◽  
Ansys Analysis ◽  
Stiffness Properties

A sandwich structure consists of three main parts i.e. the facing skins, the core and the adhesive. It acts in a way similar to that of the I- Beam. In this research, a sandwich structure has been designed with a regular hexagon honey-comb core made up of Kevlar® and face sheet of carbon fiber. The design has been modelled and the model has also been validated with the experimental and analytical method. Six different configurations of sandwich structures have been proposed. Out of these six, three configurations have the varying cell size i.e. 3.2 mm, 4 mm and 4.8 mm and the other three configurations have the varying panel width i.e. 40 mm, 45 mm and 50 mm keeping rest of the design parameters unchanged. Using ANSYS, analysis has been performed for all these six configurations and equivalent stiffness has been calculated. It has been observed that the honeycomb core cell size does not have a significant effect on the stiffness properties of a composite sandwich panel. The analysis also reveals that with the increased panel width the stiffness of composite panel increases significantly.

Mechanical responses of a composite sandwich structure with Nomex honeycomb core

2019 ◽  
Vol 38 (13) ◽  
pp. 601-615 ◽  
Author(s):  
Yue Liu ◽  
Wei Liu ◽  
Weicheng Gao ◽  
Limeng Zhang ◽  
Enjie Zhang
Keyword(s):  
Sandwich Structure ◽  
Honeycomb Core ◽  
Mechanical Responses ◽  
Composite Sandwich ◽  
Nomex Honeycomb

Impact Properties of Parts Manufactured from Fiberglass and Kevlar Composite Panels

2015 ◽  
Vol 809-810 ◽  
pp. 938-943
Author(s):  
Emilian Ionut Croitoru ◽  
Gheorghe Oancea
Keyword(s):  
Finite Element Modelling ◽  
Sandwich Panel ◽  
Composite Panel ◽  
Resin Matrix ◽  
Stress Variation ◽  
Impact Properties ◽  
Element Modelling ◽  
Composite Sandwich ◽  
Loading Case ◽  
Fuselage Skin

This paper presents a method of finite element modelling used to study the effect of laminates orientation and thickness on impact properties of a composite sandwich panel made of glass and kevlar fibers in an epoxy resin matrix. In this research, the composite sandwich panel consists of a fuselage skin panel from an aircraft having two configurations: (0/90/0/90/core/90/0/90/0) and (0/90/45/-45/core/-45/45/90/0). This panel is loaded with one uniform distributed abuse loading case and the stress variation within the composite panel for each configuration is determined.

Numerical Modelling of Impact Behavior of Composite Sandwich Panel With Honeycomb Core

2019 ◽  
Author(s):  
Shah Alam ◽  
Aakash Bungatavula
Keyword(s):  
Sandwich Panel ◽  
Sheet Thickness ◽  
Face Sheet ◽  
Honeycomb Core ◽  
Impact Performance ◽  
Composite Sandwich ◽  
The Core ◽  
The Face ◽  
Core Height ◽  
The Impact

Abstract The goal of this paper is to find the best impact response of the composite sandwich panels with honeycomb core. The focus of the study is to find the effects of changing the face sheet thickness and the core height of the sandwich panel subjected to variable velocities on impact performance. Initially, honeycomb core sandwich panel with 1mm thick face sheet is modelled in Abaqus/explicit to calculate the energy absorption, residual velocity, and deformation at four different velocities. Then, the process is repeated by changing the face sheets thickness to 2mm and 3mm to see the effects of changing the thickness on the impact performance of a composite sandwich panel. The honeycomb core height is also changed to see its effect on the performance. In all models, Al 7039 is used in the core and T1000G is used in the face sheets.

scholarly journals Numerical Modelling of a Composite Sandwich Structure Having Non Metallic Honeycomb Core

Evergreen ◽  
2021 ◽  
Vol 8 (4) ◽  
pp. 759-767
Author(s):  
Anil Kumar ◽  
Arindam Kumar Chanda ◽  
Surjit Angra
Keyword(s):  
Numerical Modelling ◽  
Sandwich Structure ◽  
Honeycomb Core ◽  
Composite Sandwich

scholarly journals DETERMINATION OF MECHANICAL PROPERTIES OF COMPOSITE SANDWICH PANEL WITH ALUMINIUM HONEYCOMB CORE

2021 ◽  
Vol 2021 (6) ◽  
pp. 5353-5359
Author(s):  
MICHAL SKOVAJSA ◽  
◽  
FRANTISEK SEDLACEK ◽  
MARTIN MRAZEK ◽  
◽  
...  
Keyword(s):  
Mechanical Properties ◽  
Numerical Simulation ◽  
Sandwich Panel ◽  
Analytical Calculation ◽  
Sandwich Panels ◽  
Honeycomb Core ◽  
Composite Sandwich Panels ◽  
Composite Sandwich ◽  
Three Point Bend Test ◽  
Honeycomb Cores

This paper deal with comparison of mechanical properties of composite sandwich panel with aluminium honeycomb core which is determined by experimental measurement, analytic calculation and numerical simulation. The goal was to compared four composite sandwich panels. The composite sandwich panels were made of two different aluminium honeycomb cores with density 32 and 72 kg.m-3 and two different layup of skin with 4 and 5 layers. The comparison was performed on a three-point bend test with support span 400 mm. This paper confirms the possibility of a very precise design of a composite sandwich panel with an aluminium honeycomb core using analytical calculation and numerical simulation.

Evaluation of skin-core adhesion bond of out-of-autoclave honeycomb sandwich structures

2012 ◽  
Vol 31 (5) ◽  
pp. 331-339 ◽  
Author(s):  
R.R. Butukuri ◽  
V.P. Bheemreddy ◽  
K. Chandrashekhara ◽  
T.R. Berkel ◽  
K. Rupel
Keyword(s):  
Cell Size ◽  
Sandwich Structures ◽  
Sandwich Panels ◽  
Core Material ◽  
Honeycomb Core ◽  
Composite Sandwich Panels ◽  
Composite Sandwich ◽  
Film Adhesive ◽  
Adhesive Thickness ◽  
Out Of Autoclave

Composite sandwich structures offer several advantages over conventional structural materials such as lightweight, high bending and torsional stiffness, superior thermal insulation and excellent acoustic damping. One failure mechanism in a composite sandwich structure is the debonding of the composite facesheets from the core structure. A well-formed adhesive fillet at the interface of the honeycomb core cell walls and the laminate is a significant factor in preventing bond failure. In the present work, honeycomb composite sandwich panels are manufactured using a low-cost vacuum-bag-pressure-only out-of-autoclave manufacturing process. CYCOM®5320 out-of autoclave prepreg is used for the facesheet laminates and FM® 300-2U film adhesive is used for the facesheet-to-core bond. The manufactured composite sandwich panels are of aerospace quality with a facesheet laminate void content of around 1%. In this study, adhesive fillet formation and adhesive mechanical strength are evaluated as a function of several different sandwich construction design variables. Both aluminum and aramid Nomex® honeycomb core materials are considered to study the effect of core cell size and core material. The effect of film adhesive thickness is studied. A process for reticulation of the adhesive is applied and studied. A quantitative investigation of the adhesive fillet geometry is carried out for all the panels. Manufactured panels are evaluated for flatwise tensile strength in accordance with test method ASTM C297. Optimized combinations of core material, core density, cell size and adhesive thickness are identified. Results show that the reticulation process improves fillet formation and increases flatwise tensile properties.

Effects of Core Height, Cell Angle and Face Thickness on Vibration Behavior of Aircraft Sandwich Structure with Honeycomb Core: An Experimental and Numerical Investigations

2021 ◽  
Vol 1039 ◽  
pp. 65-85
Author(s):  
Muhsin Jaber Jweeg ◽  
S.H. Bakhy ◽  
S.E. Sadiq
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Natural Frequency ◽  
Sandwich Structure ◽  
Damping Ratio ◽  
Design Parameters ◽  
Honeycomb Core ◽  
Element Analysis ◽  
Vibration Behavior ◽  
Core Height

The aim of the present paper is to study the vibration behavior of a sandwich structure with honeycomb core experimentally and numerically with different design parameters. The natural frequency and damping ratio were obtained. Core height, cell angle and face thickness were considered as design parameters. Finite element models for the honeycomb sandwich were developed and analyzed via ANSYS finite element analysis (FEA) software. Response Surface Method (RSM) is used to establish numerical methodology to simulate the effect of the design parameters on natural frequency and damping ration. The employment of (RSM) provides a study of the effect of design parameters on natural frequency and damping ratio, numerical modeling of them in term of design parameters and specifying optimization condition. The experimental tests were conducted on sandwich specimens for the validity goal of the previous models created via the finite element analysis. The obtained results show that the natural frequency is directly proportional to the core height and face thickness, while it is inversely proportional to cell angle, Vice versa for damping ratio. Moreover, the optimum value of natural frequency (209.031 Hz) as minimum and damping ratio (0.0320) as maximum were found at 4.8855 mm of core height, 26.770 cell angle and 0.0614 mm face thickness.

AE Monitoring of CFRP Structure during Autoclave Processing

2006 ◽  
Vol 13-14 ◽  
pp. 333-336
Author(s):  
Markku Knuuttila
Keyword(s):  
Sandwich Panel ◽  
Honeycomb Core ◽  
Adhesively Bonded ◽  
Composite Sandwich Panels ◽  
Composite Sandwich ◽  
The Core ◽  
Emission Monitoring ◽  
Structural Composite ◽  
Nomex Honeycomb ◽  
Temperature And Pressure

Large structural composite sandwich panels (approx. 2x4 m2) were found to have cracks in the honeycomb core. The core was made out of a number of Nomex honeycomb blocks having different densities. These were first machined and adhesively bonded into the final shape. The CFRP skins were then added and the sandwich panel was cured in an autoclave applying elevated temperature and pressure. Acoustic emission monitoring was done during 17 hours of processing in the autoclave using a six channel AE system. AE events from cracking of the honeycomb core were registered and could be identified in time and space. The results from AE monitoring were very useful for modifying the process parameters and overcome the cracking of the core.

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