23.3.1-R8 EFFICIENT SIZING METHODS FOR COMPOSITES PRIMARY STRUCTURES IN AUTOMOTIVE APPLICATIONS

M.HENRIK (VOLVO CAR CORPORATION), R.GUTKIN, M.OLDENBO, LE.ASP

In this paper, a set of failure criteria for Non Crimp Fabric composites are presented. The proposed failure criteria are physically based and can take into account the orthotropic character of NCF composites. The criteria are compared to experimental data.

23.3.1-R9 DAMAGE MECHANISMS OF SHORT GLASS FIBER REINFORCED POLYAMIDE 6.6 UNDER FATIGUE LOADING

E.BELMONTE (ROBERT BOSCH GMBH), M.DE MONTE, M.QUARESIMIN, C.HOFFMANN

In this paper, the state of the fiber-matrix interface and the matrix behavior of a short glass fiber reinforced polyamide (PA66-GF35) under fatigue loading were investigated.

23.3.1-R10 COMPOSITE PLATES MODELING STRATEGIES FOR THE ESTIMATION OF TRANSVERSE STRESSES

D.PASTORINO JUNQUERO (UNIVERSIDAD DE SEVILLA), A.BLÁZQUEZ, J.REINOSO, F.PARÍS

Mathematical models used to solve shell structures usually assume transverse stresses to be negligible. Nevertheless, sometimes transverse stresses could lead to the failure of the component. Herein we have analyzed some techniques that are used to compute these stress components.

23.3.1-R11 STIFFENING OF SUSTAINABLE CELLULOSE FIBRES FOR USE IN THE LIGHT WEIGHTING OF SHEET MOULDING COMPOUNDS

P.BROOKBANK (UNIVERSITY OF EXETER), L.SAVAGE

Rayon (1.5g/cm3) fibre offers significant weight savings compared to E-glass (2.5g/cm3) fibres. However, rayon is a mechanically inferior and flexible fibre in comparison to glass. Rayon treated with citric acid and formaldehyde achieved an EF of 7.0GPa and 15.5GPa respectively.

23.3.1-R12 LAMINATE DESIGN METHODS FOR CLOSED VOLUME STRUCTURES

D.JAMES (ROLLS-ROYCE)

This paper describes the process of defining composite laminates that accurately fill closed volumes such as aerofoils. The process depends on robust methods that consider numerous laminate stacking rules, to produce a requirement compliant laminate definition.

23.3.1-R13 ESTIMATION OF MECHANICAL BEHAVIOR OF NON-CRIMP FABRIC COMPOSITES WITH AN OPEN HOLE BASED ON MESH SUPERPOSITION METHOD

Y.NAKAYASU (OSAKA UNIVERSITY), Y.MATSUSHIMA, T.KURASHIKI

A new modeling method of Non-crimp fabric with a hole is proposed in order to estimate the effect of a hole’s position. The labor of change position of a hole is decreased by using mesh super position method.

23.3.1-R14 EFFECT OF 3D REINFORCEMENT ON DYNAMIC BEHAVIOR OF COMPOSITE MATERIALS USING SHPB TECHNIQUES: EXPERIMENTAL INVESTIGATION

M.TARFAOUI (ENSTA BRETAGNE), C.BOUERY, A.EL MALKI

A series of SHPB tests on 2D and 3D woven composites were presented in order to obtain a reliable comparison between the two types of composites. It was found that 3D woven composite exhibits an increase in strength.

23.3.2-R8 DEVELOPMENT OF NOVEL HEAT EFFICIENT PREHEATING PROCESS FOR HIGH CYCLE THERMOFORMING OF DISCONTINUOUS CFRTP

T.HAYASHI (THE UNIVERSITY OF TOKYO), K.HASEGAWA, H.WATAKI, J.TAKAHASHI

We investigated CFRTP impregnation mechanism to know the relationship between preheating conditions and thermoforming molding conditions. Moreover, we discuss the efficiency of fiber morphology of discontinuous CFRTP and preheating conditions to get fully impregnated CFRTP products.

23.3.2-R9 AN EXPERIMENTAL INVESTIGATION INTO FATIGUE DAMAGE DEVELOPMENT IN OPEN AND BOLTED HOLE SPECIMENS

O.NIXON-PEARSON (UNIVERSITY OF BRISTOL), SR.HALLETT

An experimental program was carried out to compare and contrast the damage development throughout the life of open-hole and bolted composite laminates under quasi-static loading and tension-tension fatigue for quasi-isotropic layups. The damage was evaluated using X-ray Computed Tomography.

23.3.2-R10 A 3D MODEL TO ANALYSE THE BEHAVIOUR OF COMPOSITE LAMINATES SUBJECTED TO OUT-OF-PLANE LOADINGS

HL.ALFONSO-MEDINA, A.UGUEN, C.BADULESCU, C.CELLARD, N.CARRERE (ENSTA BRETAGNE) et al.

The papaer presents the analysis of the behaviour of adhesively-bonded composite laminates subjected to tensile-shear out-of-plane loadings. The experimental approach is based on the modified Arcan. An inverse FE analysis permits to dtermine the out-of-plane failure envelope.

23.3.2-R11 ALL-CELLULOSE COMPOSITE WITH HIGH THERMAL CONDUCTIVITY USING NANODIAMONDS

E.MORIO (KOBE UNIVERSITY), C.HONGO, M.KOTERA, T.NISHINO, K.GOTO et al.

In this study, we immersed uniaxially aligned cellulose fibers in nanodiamond(ND) aqueous suspension and dried, followed by impregnation with cellulose solution. This all-cellulose composite with ND is environmentally friendly. Structure and properties of the composite were investigated.

23.3.2-R12 AN APPROACH TOWARDS AN OPTIMAL DESIGN OF COMPOSITE STRUCTURES

B.GOLLER (INTALES GMBH), M.GRATT, C.ELSEL

The paper shows the development of an efficient, fast and reliable optimizer for composite and metallic parts of lightweight structures. The algorithm aims at identifying optimal configurations of structural parts concerning thickness, fibre orientation, number of plies and fastener diameters.

23.3.2-R13 ACCURATE NUMERICAL SIMULATION OF KINKING CRACKS IN COMPOSITES

ST.PINHO (IMPERIAL COLLEGE LONDON), B.CHEN, N.CARVALHO, P.BAIZ, E.TAY

This paper presents a new method suitable for modelling kinking discontinuities. The proposed method can predict the transition from matrix cracking to delamination in cross-ply composite laminates by accurately representing T-shaped cracks inside a single finite element.

23.3.2-R14 VIRTUAL ASSESSMENT OF A COMPOSITE LAMINATE WITH INTERLEAVED NANOFIBROUS MAT UNDER IMPACT LOADING

G.GIULIESE (UNIVERSITY OF PARMA), A.PIRONDI, E.FURLOTTI, A.ZUCCHELLI, R.PALAZZETTI

The aim of this work is to simulate the impact strength of a composite laminate with nanomodified interplies of different strength, in the perspective of tailoring the interply delamination and the impact energy absorbed by the composite.

23.3.3-R8 FINITE ELEMENT ANALYSIS OF CFRTP HOLLOW BEAM UNDER FLEXURAL LOAD FOR AN APPLICATION TO VEHICLE BODY STRUCTURE

T.OHORI (THE UNIVERSITY OF TOKYO), T.MATSUO, K.FURUKAWA, J.TAKAHASHI

Experimental and numerical studies for both CFRTP rectangular specimen and several kinds of hollow beams under flexural load were conducted to verify both mechanical properties obtained by small specimen and material model used in FEA.

23.3.3-R9 AN ENERGY-BASED METHOD FOR NUMERICAL FATIGUE ANALYSIS FOR MULTIDIRECTIONAL CARBON FIBER REINFORCED PLASTICS

P.WAGNER (BMW GROUP), T.BRUDER, M.MAY, F.BACHMANN

This work describes experiments on multiaxial fibre reinforced plastic laminates, which were performed in order to create a model for the numerical fatigue analysis. The presented tests characterise the fatigue behaviour of chosen laminates for unidirectional loading conditions.

23.3.3-R10 INVESTIGATING DELAMINATION MIGRATION IN MULTIDIRECTIONAL TAPE LAMINATES

MF.PERNICE (UNIVERSITY OF BRISTOL), JG.RATCLIFFE, NV.DE CARVALHO, SR.HALLETT

A novel test method and specimen configuration were employed to isolate a single delamination migration at a 0/θ interface. Tests allowed to investigate details of the migration process and understand the fundamental driving forces for delamination migration in composite laminates.

23.3.3-R11 INFLUENCE OF PROCESSING CONDITIONS ON THE MORPHOLOGY AND PROPERTIES OF POLYMER/MICROFIBRILLATED CELLULOSE COMPOSITES

C.PLUMMER (ECOLE POLYTECHNIQUE FÉDÉRALE DE LAUSANNE (EPFL)), S.GALLAND, PE.BOURBAN, Y.LETERRIER, JA.MANSON

Solvent processing of polymer/nanofibrillated cellulose (NFC) blends leads to homogeneous dispersions and significant reinforcement. Cellular networks of agglomerated NFC obtained by wet-comingling also provide significant reinforcement, but break-up of these networks into isolated aggregates during extrusion severely reduces their effectiveness.

23.3.3-R12 OSIRHYS IV PROJECT: QUALIFICATION AND OPTIMISATION OF 700 BAR COMPOSITE PRESSURE VESSEL

B.GENTILLEAU (CEA), S.VILLALONGA, F.NONY, H.GALIANO

The goal of OSIRHYS IV project is to develop and validate models and methods for composite high pressure design. The qualification process involves a comparison between experimental and numerical results on a tank which are also presented in this study.

23.3.3-R13 A MULTISCALE METHOD FOR THE ANALYSIS OF FIBER REINFORCED COMPOSITE STRUCTURES USING THE CW APPROACH

M.MAIARU (UNIVERSITY OF MICHIGAN), E.CARRERA, P.MEYER, AM.WAAS

A hierarchical multiscale approach for the analysis of fiber-reinforced composite structures is presented in this work. Two scales are taken into account, the macro-scale is modeled through 3D elements while the CW approach is used at the microscale level.

23.3.3-R14 COMPUTATIONAL MODELING OF IMPACT DAMAGE IN LAMINATED COMPOSITE PLATES

A.AHMED (DELFT UNIVERSITY OF TECHNOLOGY), LJ.SLUYS

A time-dependent laminate failure model is presented to simulate impact induced damage. The computational framework uses solid-like shell elements to model individual plies of laminated plates and allows for mesh-independent dynamic crack propagation through FEM mesh of shells.

23.3.4-R8 DESIGN OF CARBON FIBER MAT REINFORCED THERMOPLASTICS BY CONTROLLING FIBER/MATRIX ADHESION AND VOLUME FRACTION OF FIBER

W.NAGATSUKA (THE UNIVERSITY OF TOKO), N.HIRANO, H.MURAMATSU, Y.TAKEBE, A.TSUCHIYA et al.

The effect of resin modification or Vf on mechanical properties of CFRTP was examined in order to design the optimum CMT. The relationship among CF/PP interfacial adhesion or Vf and mechanical properties was illustrated with quantitatively about CMT.

23.3.4-R9 LIFETIME PREDICTION WITH ACOUSTIC EMISSION DURING STATIC FATIGUE TESTS ON CERAMIC MATRIX COMPOSITE AT INTERMEDIATE TEMPERATURE UNDER AIR

N.GODIN (INSA DE LYON), E.MAILLET, M.R'MILI, P.REYNAUD, G.FANTOZZI et al.

This paper proposes a new approach to the analysis of acoustic emission data for lifetime prediction. The energy of signals is used to evaluate in real-time energy attenuation due to damage accumulation during static fatigue tests on ceramic matrix composites.

23.3.4-R10 EFFECT OF STITCHING PARAMETER ON MODE II DELAMINATION PROPERTIES OF VECTRAN STITCHED COMPOSITES

J.HERWAN (TOKYO METROPOLITAN UNIVERSITY), A.KONDO, S.MOROOKA, N.WATANABE

Moderately stitched laminates has negligible influence on energy release rate (Gii), meanwhile densely stitched laminates improved Gii significantly. Furthermore, stitched thread thickness did not play notable role on moderately stitched specimens, however it exhibit significant effect in densely stitched specimen.

23.3.4-R11 POLYMER COMPOSITE WITH MICRO- AND NANOCELLULOSE FOR ARTWORK PROTECTION AND RESTORATION

A.CATALDI (UNIVERSITY OF TRENTO), A.DORIGATO, F.DEFLORIAN, L.BERGLUND, A.PEGORETTI

Micro- and nanoomposites were prepared using Aquazol®500 as a polymeric matrix and a microcrystalline cellulose, and cellulose nanocrystals, as reinforcing agents, to be applied as canvas-lining adhesives. Single–lap shear tests showed a reduction of the adhesives compliance as filler increases.

23.3.4-R12 MULTI-OBJECTIVE AND MULTI-CONSTRAINT OPTIMISATION OF VARIABLE STIFFNESS COMPOSITE LAMINATES

D.PEETERS (DELFT UNIVERSITY OF TECHNOLOGY), S.HESSE, M.ABDALLA

An algorithm to optimise the fibre angle distribution of variable stiffness laminates is presented where, for manufacturability, the local and/or average norm of the gradient is constrained. Optimised manufacturable laminates with 63% higher buckling load than conventional laminates are found.

23.3.4-R13 AN SGBEM IMPLEMENTATION OF CRACK PROPAGATION AT A FIBRE-MATRIX INTERFACE

J.KŠIŇAN (TECHNICAL UNIVERSITY OF KOŠICE, FACULTY OF CIVIL ENGINEERING), R.VODIČKA

A numerical failure model of a cohesive fibre-matrix interface is presented. The contribution discusses the failure mechanism of a fibre bundle embedded in an matrix subjected to transverse load. The numerical analysis investigates the crack propagation at the fibre-matrix interface.

23.3.4-R14 CRASHWORTHINESS OF INTEGRATED CRASH-BOX AND BUMPER BEAM MADE BY DIE-FORMINJG COMPOSITE

EG.KORICHO (POLITECNICO DI TORINO), G.BELINGARDI, A.BEYENE, B.MARTORANA

Detailed material characterization of three materials i.e. classic glass-mat-reinforced thermoplastics (GMT), GMtex (GMT reinforced with a fabric) and GMT-UD (GMT reinforced with unidirectional oriented glass fiber layer ),were conducted and their performancebfor substituting the current metallic bumper were numerically assessed.