Multi-Level Modeling of Low Velocity, Low Energy Impact on Metal-Skinned Sandwich Structure

2006 ◽  
Author(s):  
B. Castanie´ ◽  
C. Bouvet ◽  
J.-J. Barrau ◽  
P. Thevenet
Keyword(s):  
Phenomenological Study ◽  
Sandwich Structures ◽  
Element Model ◽  
Honeycomb Structure ◽  
Low Energy ◽  
Low Velocity ◽  
Uniform Compression ◽  
Energy Impact ◽  
Nonlinear Springs ◽  
Static Indentation

The research objective is to model the low velocity/low energy impact on sandwich structures with metallic skins. A progressive approach is carried out by considering first the honeycomb core alone, then static indentation on sandwich structures and finally a dynamic analysis. During the first step, a phenomenological study of the behavior of honeycomb subjected to crushing is completed. It appears that local rotations and cell edges plays an important role in the crushing phenomenon. It is then possible to propose a simple analytical model able to represent the indentation of honeycomb alone for various indenter geometries by modelling only the cell edges behavior. The compression law of the cell edges is identified by a basic uniform compression test. This key-idea is then used to create a finite element model using a grid of nonlinear springs to represent the honeycomb structure. The contact law of static indentation tests of metal-skins Nomex™ honeycomb sandwich structures can thus be found numerically and agree well with the experiments. Finally, this contact law can be used to model dynamic impacts which demonstrates the static/dynamic equivalence for this range of impact and structures.

Numerical Simulation of Low Velocity Impact on Pin-Reinforced Foam Core Sandwich Panel

2017 ◽  
Vol 742 ◽  
pp. 673-680
Author(s):  
M. Adli Dimassi ◽  
Axel S. Herrmann
Keyword(s):  
Sandwich Structures ◽  
Element Model ◽  
Low Velocity Impact ◽  
Foam Core ◽  
Low Velocity ◽  
Industrial Sectors ◽  
Out Of Plane ◽  
Scale Modelling ◽  
Cohesive Zone Elements ◽  
The Impact

The use of sandwich structures is well established in industrial sectors where high stiffness and strength combined with lightweight are required, like in marine, wind turbine and railway applications. However, the vulnerability of sandwich structures to low-velocity impacts limits its use in primary aircraft structures. Pin reinforcement of the foam core enhances the out-of-plane properties and the damage tolerance of the foam core. In this paper, a finite element model is proposed to predict the impact behaviour of pin-reinforced sandwich structure. An approach based on the building block approach was used to develop the model. Multi-scale modelling in the impact region that considers the delamination of the face sheet using cohesive zone elements was employed to increase the accuracy of the simulation. Impact tests were performed to validate the numerical model. A good agreement between numerical and experimental results in terms of contact-force displacement history and failure mode was found.

Low Energy Impact Damage Modes in Aluminum Foam and Polymer Foam Sandwich Structures

2006 ◽  
Vol 8 (5) ◽  
pp. 365-379 ◽  
Author(s):  
Paul Compston ◽  
Millicent Styles ◽  
Shankar Kalyanasundaram
Keyword(s):  
Aluminum Foam ◽  
Sandwich Structures ◽  
Impact Damage ◽  
Low Energy ◽  
Polymer Foam ◽  
Energy Impact

scholarly journals Residual compression property and response of honeycomb sandwich structures subjected to single and repeated quasi-static indentation

2021 ◽  
Vol 60 (1) ◽  
pp. 404-417
Author(s):  
Hangyu Ye ◽  
Xiangjun Dai ◽  
Tianyu Yuan ◽  
Jilei Zhou ◽  
Jipeng Zhang ◽  
...  
Keyword(s):  
Sandwich Structures ◽  
Three Dimensional ◽  
Correlation Method ◽  
Image Correlation ◽  
Low Velocity Impact ◽  
Low Velocity ◽  
Governing Parameter ◽  
Honeycomb Sandwich ◽  
Static Indentation ◽  
Residual Compression

Abstract This paper investigated the response and residual compression properties of honeycomb sandwich structures subjected to single quasi-static indentation (QSI) and repeated QSI (RQSI). The damage depth after repeated low-velocity impact (LVI) was considered as the governing parameter during the QSI experiments. Three-dimensional digital image correlation method was applied to determine deformation of the front panels after LVI and QSI to describe damage to honeycomb structures. For specimens with the same depth, it is found that the residual strength of QSI was less than that of LVI and close to that of RQSI. Results indicated that it is more reasonable to describe the damage by volume than by depth.

scholarly journals INTERLAMINAR AND INTRALAMINAR DAMAGE MECHANISMS OF IMPACT RESISTANT AIRCRAFT MATERIALS UNDER LOW‐ENERGY IMPACT

Aviation ◽  
2006 ◽  
Vol 10 (3) ◽  
pp. 3-8 ◽  
Author(s):  
Neringa Keršienė ◽  
Antanas Žiliukas
Keyword(s):  
Woven Fabrics ◽  
Low Energy ◽  
Matrix Cracking ◽  
Woven Fabric ◽  
Low Velocity Impact ◽  
Front Face ◽  
Low Velocity ◽  
Composite Systems ◽  
Energy Impact ◽  
Reinforced Composite

For low-velocity impact, drop‐weight impact tests performed by EADS (European Aeronautic Defence and Space Company) Corporate Research Center Germany have been carried out for 2‐D woven E‐Glass/epoxy composite systems to determine material response as a function of absorbed energy and damaged area. Nondestructive techniques like visual inspection and analysis of impact response of the woven fabric laminates at different energy levels are utilized to assess the initiation and progression of interlaminar and intralaminar damage. The dominant damage modes for woven reinforced composite systems were found to be matrix cracking with branching into the adjacent layers, intralaminar cracking by mixture of localized matrix shear and matrix/fibre interfacial debonding, front face indentation, and back face fibre damage. The use of woven fabrics as opposed to cross‐ply unidirectional prepreg tapes is specifically discussed from the point view of microstructure and property. In the case of low‐energy impact, damage resistance under impact loading of woven and multiaxial non‐crimp fabrics is presented and compared. The assumption that shear‐response dominated for woven reinforced composite systems was found to be in good agreement with the experimental results.

Multiscale Damage Modeling on Aeronautical Composite Under Low Energy Impact

2018 ◽  
Vol 09 (03) ◽  
pp. 1840003
Author(s):  
Michele Buonsanti
Keyword(s):  
Composite Material ◽  
Large Body ◽  
Fem Analysis ◽  
Low Energy ◽  
Low Velocity Impact ◽  
Composite Panels ◽  
Low Velocity ◽  
Element Analysis ◽  
Energy Impact ◽  
The Impact

The purpose in this paper is to investigate about the behavior of aeronautics composite material subjected to a low energy impact. Low velocity impact in aircraft composite panels is a matter of concern in modern aircraft and can be used either from maintenance accidents tools or in-flight impact with debris. The proposed study considers the dynamics of impact between a small piece of granular material and a large body of composite material. The principal aim is to simulate the impact of runway debris throw-up by the landing gear against an airplane structure. In this simulation, I want to investigate on CFRP composite panels affected by granular particles at low speed in theoretical and experimental tests. The finite element analysis, initially on the macroscale and subsequently on the microscale, shows the damage inside the composite according to the experimental results, but by itself, this classic numerical approach is little suitable to investigate the complete phenomenon. Developing the question, in first step by the classical approach, appears difficult on macro and microscale relationship besides their reciprocal influence over the deformation field. To resolve the last question, I will perform the first step on macroscale FEM analysis and then reduce from the size and effects over an opportune created RVE, such that microscale main effects as local delamination can be reproduced.

scholarly journals Effect of nanofillers on low energy impact performance of sandwich structures with nanoreinforced polyurethane foam cores

2014 ◽  
Vol 16 (2) ◽  
pp. 173-194 ◽  
Author(s):  
Sophia Sachse ◽  
Manohar Poruri ◽  
Francesco Silva ◽  
Slawomir Michalowski ◽  
Krzysztof Pielichowski ◽  
...  
Keyword(s):  
Polyurethane Foam ◽  
Sandwich Structures ◽  
Low Energy ◽  
Impact Performance ◽  
Energy Impact

Low-energy drop weight performance of cellular sandwich panels

2015 ◽  
Vol 21 (4) ◽  
pp. 433-442 ◽  
Author(s):  
Li Yang ◽  
Ola A Harrysson ◽  
Harvey A West II ◽  
Denis R. Cormier ◽  
Chun Park ◽  
...  
Keyword(s):  
Energy Absorption ◽  
Sandwich Panel ◽  
Sandwich Structures ◽  
Sandwich Panels ◽  
Low Energy ◽  
Cellular Structures ◽  
Content Type ◽  
Powder Bed ◽  
Energy Impact ◽  
Drop Weight

Purpose – The aim of this study is to perform a comparative study on sandwich structures with several types of three-dimensional (3D) reticulate cellular structural core designs for their low-energy impact absorption abilities using powder bed additive manufacturing methods. 3D reticulate cellular structures possess promising potentials in various applications with sandwich structure designs. One of the properties critical to the sandwich structures in applications, such as aerospace and automobile components, is the low-energy impact performance. Design/methodology/approach – Sandwich samples of various designs, including re-entrant auxetic, rhombic, hexagonal and octahedral, were designed and fabricated via selective laser sintering (SLS) process using nylon 12 as material. Low-energy drop weight test was performed to evaluate the energy absorption of various designs. Tensile coupons were also produced using the same process to provide baseline material properties. The manufacturing issues such as geometrical accuracy and anisotropy effect as well as their effects on the performance of the structures were discussed. Findings – In general, 3D reticulate cellular structures made by SLS process exhibit significantly different characteristics under low-energy drop weight impact compared to the regular extruded honeycomb sandwich panels. A hexagonal sandwich panel exhibits the largest compliance with the smallest energy absorption ability, and an octahedral sandwich panel exhibits high stiffness as well as good impact protection ability. Through a proper geometrical design, the re-entrant auxetic sandwich panels could achieve a combination of high energy absorption and low response force, making it especially attractive for low-impact protection applications. Originality/value – There has been little work on the comparative study of the energy absorption of various 3D reticulate cellular structures to date. This work demonstrates the potential of 3D reticulate cellular structures as sandwich cores for different purposes. This work also demonstrates the possibility of controlling the performance of this type of sandwich structures via geometrical and process design of the cellular cores with powder bed additive manufacturing systems.

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