Thermal Behavior Of Natural Fiber Mat Hybrid Composite For Tooling Materials.

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UNIVERSITI TEKNIKAL MALAYSIA MELAKA

THERMAL BEHAVIOR OF NATURAL FIBER MAT HYBRID

COMPOSITE FOR TOOLING MATERIALS

This report submitted in accordance with requirement of the Universiti Teknikal Malaysia Melaka (UTeM) for the Bachelor Degree of Manufacturing Engineering

(Engineering Materials) (Hons.)

NOR FARIHA BINTI SOHOD B 051010218

890109-04-5112

FACULTY OF MANUFACTURING ENGINEERING 2013

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UNIVERSITI TEKNIKAL MALAYSIA MELAKA

BORANG PENGESAHAN STATUS LAPORAN PROJEK SARJANA MUDA TAJUK: Thermal Behavior of Natural Fiber Mat Hybrid Composite for Tooling Materials

SESI PENGAJIAN: 2012/13 Semester 2 Saya NOR FARIHA BINTI SOHOD

mengaku membenarkan Laporan PSM ini disimpan di Perpustakaan Universiti Teknikal Malaysia Melaka (UTeM) dengan syarat-syarat kegunaan seperti berikut: 1. Laporan PSM adalah hak milik Universiti Teknikal Malaysia Melaka dan penulis. 2. Perpustakaan Universiti Teknikal Malaysia Melaka dibenarkan membuat salinan

untuk tujuan pengajian sahaja dengan izin penulis.

3. Perpustakaan dibenarkan membuat salinan laporan PSM ini sebagai bahan pertukaran antara institusi pengajian tinggi.

4. **Sila tandakan (√)

SULIT

TERHAD

TIDAK TERHAD

(Mengandungi maklumat yang berdarjah keselamatan atau kepentingan Malaysiasebagaimana yang termaktub dalam AKTA RAHSIA RASMI 1972)

(Mengandungi maklumat TERHAD yang telah ditentukan oleh organisasi/badan di mana penyelidikan dijalankan)

Alamat Tetap:

NO. 127, Kampung Baru Ayer Keroh, 75450 Melaka.

Tarikh: _________________________

Disahkan oleh:

Cop Rasmi:

Tarikh: _______________________ ** Jika Laporan PSM ini SULIT atau TERHAD, sila lampirkan surat daripada pihak berkuasa/organisasi berkenaan dengan menyatakan sekali sebab dan tempoh laporan PSM ini perlu dikelaskan sebagai SULIT atau TERHAD.

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DECLARATION

I hereby, declared this report entitled “ Thermal Behavior of Natural Fiber Mat Hybrid Composite for Tooling Materials” is the results of my own research except as cited in references.

Signature :

Author‟s Name : NOR FARIHA BINTI SOHOD

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APPROVAL

This report is submitted to the Faculty of Manufacturing Engineering of UTeM as a partial fulfillment of the requirements for the degree of Bachelor of Manufacturing Engineering (Engineering Materials) (Hons.). The members of the supervisory committee are as follow:

……… (MISS CHANG SIANG YEE)

……… (PROF. DR. QUMRUL AHSAN)

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ABSTRAK

Pengeluar industri aeroangkasa memerlukan peralatan yang bersaiz besar untuk menghasilkan komponen earoangkasa. Penggunaan peralatan gentian sintetik komposit adalah lebih ringan berbanding peralatan logam tetapi ia mahal and sukar untuk di kitar semula. Projek ini bertujuan untuk memperkenal gabungan gentian semulajadi dengan gentian sintetik untuk menghasilkan bahan peralatan. Projek ini adalah untuk fabrikasi jut/ kaca gentian bertetulang epoksi komposit lamina dengan mengubah orientasi gentian dan menyusun urutan melalui kaedah sapuan tangan dan pembalut vakum, mencirikan tetulang dari segi fizikal dan mekanikal dan haba untuk menyiasat perubahan bentuk dan kestabilan dimensi komposit apabila terdedah kepada haba berulang kali. Orientasi lamina diubah (0/90º) dan (-45/45º), dan disusun sehingga 7 dan 9 lapisan dengan urutan yang berbeza. Komposit lamina di uji dari segi penyerapan air, lenturan dan pendedahan kepada haba berulang kali. Pemeriksaan mikroskopi juga dijalankan untuk melihat mod kegagalan lenturan komposit lamina sebelum dan selepas terdedah kepada haba. Ia telah mendapati tanpa mengira orientasi dan susunan urutan,jut/kaca gentian bertetulang epoksi komposit lamina memiliki kepadatan yang rendah dan kapasiti penyerapan air yang tinggi menyebabkan pembengkakan pada lamina komposit. Ujian pendedahan kepada haba 180º C berulang kali telah menyebabkan pengurangan kestabilan dimensi yang disebabkan oleh pekali yang berbeza pengembangan haba (CTE) bahan dan penguraian awal pada komposit lamina. Degradasi membuktikan kekuatan lenturan komposit lamina bekurang selepas 15 kitaran haba. Walau bagaimanapun, kekukuhan komposit lamina menunjukkan peningkatan dan ini boleh dikaitkan dengan kesan pengerasan belaku selepas terdedah kepada haba berulang kali. Mod kegagalan menunjukkan nyahikatan, delamination dan serat penyambung di kenalpasti pada komposit lamina.

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ABSTRACT

Aerospace industry manufacturers require large tools to fabricate large aerospace components. The use of synthetic fiber reinforced composite tooling provides a lightweight solution as compared to metal tooling, yet it is expensive and not recyclable. This project serves to introduce natural fiber as partial replacement in synthetic fiber composite for tooling materials. This project aimed to fabricate jute/glass fiber reinforced epoxy laminate composite by varying fiber orientation and stacking sequence through hand lay-up and vacuum bagging technique, characterize the physical and mechanical behaviors of the fabricated laminate composite and investigate the deformation behavior associated with dimensional stability of the composite when subjected to thermal cycling. The orientation of the laminae varied at (0/90º) and (-45/45º), and stacked up to 7 and 9 plies with different sequence. The laminate composite was subjected to water absorption, flexural and thermal cycling testing. Microscopy examinations were also carried out to observe the deformation behaviour as well as the flexural failure mode of the laminate composite prior to and post thermal cycling. It was found that the regardless of orientation and stacking sequence, jute/glass fiber reinforced epoxy laminate composite possessed low density and high water absorption capacity which caused swelling on the laminate composite. The thermal cycling test conducted at 180°C resulted in reduction of dimensional stability due to different coefficient of thermal expansion (CTE) of the constituent materials and initial degradation of the laminate composite. Degradation was evidenced as the flexural strength of the laminate composite reduced after 15 thermal cycles. However, the stiffness of the laminate composite showed improvement and this can be attributed to effect of further curing that took place in the composite after thermal cycling. The failure mode showed debonding, delamination and fiber bridging on laminate composite.

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iii

DEDICATION

To my beloved parents, supervisor, co-supervisor, siblings, lecturers and friends.

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ACKNOWLEDGEMENT

I would like to thank the Almighty for His mercy and His grace that I managed to complete this individual assignment of subject BMFG 4932 successfully. All plans to complete this task could be run smoothly. In this opportunity, I would like to express my deepest appreciation and thanks to Miss Chang Siang Yee for her helpful assistance and guidance on this task to meet the specified requirements. Her guidance did help me to create more ideas and improvements in producing the satisfactory work. Not forgetting to express my appreciation and thanks to Prof.Dr. Qumrul Ahsan who is my co-supervisor and technicians involved for giving me the help in accomplishing the task given. Also, thanks to UTeM library staffs for their contribution in the matters related to resources from the library. Their cooperation could definitely add the great value in this report. Finally, once again I wish to express my thanks to all those involved, either directly or indirectly.

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TABLE OF CONTENT

Abstrak i

Abstract ii

Dedication iii

Acknowledgement iv

Table of Content v

List of Tables viii

List of Figures ix

List Abbreviations, Symbols and Nomenclatures xii

CHAPTER 1: INTRODUCTION 1

1.1 Background 1

1.2 Problem Statement 3

1.3 Objectives 3

1.4 Scope 4

CHAPTER 2: LITERATURE REVIEW 5

2.1 Tooling 5

2.1.1 Metallic Tooling 6

2.1.2 Composite Tooling 7

2.1.2.1 Polymer Matrix 8

2.1.2.2 Fiber Reinforcement 11

2.2 Hybrid Composites 13

2.2.1 Types of Fiber 14

2.2.1.1 Synthetic Fiber – Glass Fiber 16 2.2.1.2 Natural Fiber – Jute Fiber 18

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2.3 Hand Lay-up and Vacuum Bagging 23

2.4 Effect of Stacking on Hybrid Composites 25

2.4.1 Physical Properties 25

2.4.2 Mechanical Properties 27

2.4.3 Thermal Properties 29

2.5 Effect of Orientation on Hybrid Composites 31

2.5.1 Dimensional Stability 31

2.5.2 Thermal Properties 34

CHAPTER 3: METHODOLOGY 36

3.1 Materials 36

3.1.1 Epoxy Resin and Hardener 37

3.1.2 Glass Fiber 38

3.1.3 Jute Fiber 38

3.2 Preparation of Raw Material 39

3.3 Characterization of Raw Materials 40

3.3.1 Electronic Densimeter 40

3.3.2 Scanning Electron Microscope (SEM) 41 3.4 Fabrication of Laminated Hybrid Composites 41 3.4.1 Preparation of Stacked Hybrid Laminate Composite 42 3.4.2 Fabrication of hybrid laminate composite 43

3.5 Sample Preparation of Composites 45

3.6 Characterization of Composites 46

3.6.1 Physical Properties 46

3.6.1.1 Density 46

3.6.1.2 Water Absorption 46

3.7 Testing 47

3.7.1 Thermal Cycling 47

3.7.2 Flexural Test 48

3.8 Microscopic Observation 50

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vii

CHAPTER 4: RESULTS & DISCUSSION 53

4.1 Characterization of Raw Materials 53

4.1.1 Density 54

4.1.2 Scanning Electron Microscopy (SEM) 55

4.2 Characterization of Composites 55

4.2.1 Density 56

4.2.2 Water Absorption 57

4.3 Testing of Composites 60

4.3.1 Thermal Cycling 61

4.3.2 Flexural Testing 66

CHAPTER 5: CONCLUSIONS & FUTURE WORK 74

5.1 Conclusions 74

5.2 Future Work 76

REFERENCES 77

APPENDICES 84

Gantt chart PSM 1 84

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viii

LIST OF TABLES

2.1 2.2 2.3 2.4 2.5

Typical Properties of Tooling Materials Some typical properties of thermosets Properties of fiber materials

Chemical composition of jute fibers Physical properties of some natural fibers

7 11 17 19 20

3.1 3.2

3.3

Product specification of Epoxy Resin (DM15 (F3)

Fiber mat orientation and staking sequence of jute/glass fiber reinforced epoxy

Detailed description on fabrication of hybrid laminate composite

37 42

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LIST OF FIGURES

2.1 Arrangement of polymer chain: (a) cross-linked, (b) linear, (c) branched. 9 2.2 2.3 2.4 2.5 2.6 2.7 2.8 2.9 2.10 2.11 2.12 2.13 2.14 2.15 2.16

Chemical structure of typical epoxy. Typical reinforcement types.

Classification of natural and synthetic fibers.

(a)Basic unit of SiO2, (b) combination of two units, (c) the

structure of glasses is a three dimensional network based on silica but usually modified by the presence of other elements.

Chemical structure of cellulose. Laminated composite.

Lamina and laminate lay-up. Hand Lay-up.

Vacuum bagging with outlet vacuum line and resin feed line. Vacuum bagging set up schematic.

SEM image of tensile fractured surface of laminate under flexural load.

TGA results for treated/untreated hybrid composites of sisal/glass.

DSC results for treated/untreated composites sisal/glass at 2cm fiber length.

Thermally induced loads.

Percentage of dimensional change with temperature indicates shrinkage at first heating cycle and near linear behaviour in second heating cycle.

10 15 17 20 21 22 23 24 24 28 30 31 32 34

3.1 Glass fiber ma.t 38

3.2 Jute fiber mat. 38

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3.4 Dessicator. 39

3.5 Electronic densimeter. 40

3.6 3.7a 3.7b 3.8 3.9 3.10 3.11 4.1 4.2 4.3 4.4 4.5 4.6 4.7 4.8 4.9

Scanning Electron Macroscope.

Dimensions of water absorption test specimen.

Dimensions of flexural and dimensional stability test specimen. Oven.

Universal Testing Machine. Digital Imaging Microscopy. Flow chart methodology

SEM micrograph of bleached jute fiber under magnification of 300x.

Density of jute/glass fiber reinforced composite at different orientation and stacking sequence.

Water absorption of jute/glass fiber composite at different orientation and stacking sequence for duration of three weeks. Jute/glass fiber reinforced laminate composite experienced swelling after water absorption test.

Change in thickness of jute/glass fiber reinforced epoxy laminate composite at different composition.

Thickness loss of (a) 7 plies and (b) 9 plies of jute/glass fiber reinforced epoxy laminate composite at different orientation and stacking sequence.

Different weight loss versus number of heating cycles of (a) 7 plies (b) 9 plies of jute/glass fiber reinforced epoxy laminate composite at different orientation and stacking sequence on 7 plies.

Discoloration occurred after heating for 15 cycles on (a)

jute/glass fiber reinforced epoxy laminate composite (S7 – 2) and (b) glass fiber reinforced epoxy laminate composite.

Cross section of (a) unaged, (b) aged of S9 – 1 and (c) unaged, (c)

41 45 45 48 48 50 51 55 56 57 58 59 62 64 65 66

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xi 4.10

4.11

4.12

4.13

aged of S9 – 2 lamiante composite after 15 thermal cycles. Comparison of (a) flexural strength, (b) flexural modulus and (c) stiffness of laminate composite at 0 thermal cycle.

Fracture mode of jute /glass fiber reinforced epoxy laminate composite at 0 thermal cycle (a) S7 – 1 (GGGGGGG), (b) S7

– 3 (GGG‟GG‟GG), (c) S7 –2 (GJ‟GJ‟GJ‟G) and (d) S7 – 4

(GJ‟GJGJ‟G).

Comparison of (a) flexural strength, (b) flexural modulus and (c) stiffness of jute/glass fiber reinforced epoxy laminate composite at different orientation and stacking sequence, prior to and post thermal cycling.

Cross section of (a) 0 cycle on S9 – 1, (b) 15 cycles on S9 – 1, (c) 0 cycle on S9 – 4 and (d) 15 cycles on S9 – 4 of glass fiber reinforced epoxy laminate composite at different orientation and stacking sequence after flexural test.

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xii

LIST OF ABBREVIATIONS, SYMBOLS AND

NOMENCLATURE

ASTM - American Standard Test method CTE - Coefficient of thermal expansion DSC - Differential Scanning Calorimetry FRP - Fiber Reinforced Plastics

NASA - National Aeronautics and Space Administration PLA - Poly (lactic acid)

PMC - Polymer Matrix Composites PVC - Polyvinyl chloride

SE - Secondary electron

SEM - Scanning Electron Microscope SiO2 - Silica

SME - Society of Manufacturing Engineers TGA - Thermogravimetric Analysis

UTM - Universal Testing Machine UV - Ultra-violet light

Mi - immersion weight Mo - original weight Mw - weight gain

Pmax - maximum load at failure (N) σmax - maximum stress

ºC - degrees Celsius 0

F - degrees Fahrenheit W/mK - thermal conductivity

m/m/ ºC - coefficient of thermal expansion g/cm3 - density

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xiii J/g.K - thermal mass

in - inch

mm - milimeter

µ - micron

GPa - gigapascal MPa - megapascal MPam1/2 - fracture toughness

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1 This chapter introduces the background, problem statement, objectives as well as the scope of the study.

1.1 Background

Nowadays, the aerospace industry manufactures increasingly larger components which require the use of larger tools. High performance, cost effective materials are used to produce the tools to ensure the quality of the end-product and sustainability of the tooling. Traditionally, metals have been used as tooling materials for composite processing. However, the weight of metal tooling has become an issue particularly for manufacturing of large aerospace components. Consequently, lightweight materials would be preferred to accomplish this task. Introduction of hybrid composite materials as tooling materials has weight advantage over the metals and produces stronger components. Hybrid composite which is made of two or more different kinds of fiber in single matrix, provides better combination of properties than composite containing single fiber (Callister., 2006).

At present, synthetic fiber reinforced composite is widely used by manufacturers to produce tooling. The drawbacks of the synthetic composites tooling are associated with its high cost and limitation of recyclability. Satyanarayana et al. (2009) as cited in Jawaid et al. (2011) highlighted that glass fiber costs approximately 1200 –

INTRODUCTION

CHAPTER 1

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2 1800US$/tones which is almost twice the price of the natural fibers. Besides, according to National Composite Network (2006), the issue of recycling composite poses great impact on the environment. This is due to the lack of clear and well-developed recycling routes (logistics, infrastructure and recycling technologies). Additionally, disposal of carbon or glass fiber by incineration is detrimental to our mother earth (Nishino et al., 2003).

To circumvent the problem, green hybrid composite tooling is an alternative by partial replacement of the synthetic fiber with the presence of natural fiber in the composite tooling. Incorporation of natural fibers in the composite presents a number of advantages such as low tool wear, low density, cheaper cost, abundance availability and the most importantly its biodegradability (Akil et al., 2011).

Natural fiber reinforced composites have found applications in automobile and furniture industries as the composites possess comparable mechanical properties to that of glass fiber reinforced composites (Sabah et al., 2012). Thus, the venture of green hybrid composite into composite tooling is highly promising. Among the natural fibers available in the market, jute, flax and coir show the prominent properties in engineering applications.

Though so, the challenge of utilization green hybrid composite tooling lies on the difference of thermal mass and coefficient of thermal expansion between the natural and synthetic fiber. The varying fiber orientation and stacking sequence of glass and natural fiber significantly affects the hybrid composites (Patel et al., 2011). Ahmed and Vijayarangan (2008) revealed that the arranging jute fiber plies at the middle of the hybrid composites led to improved flexural strength. According to Tezvergil et al. (2003), the direction perpendicular to fiber orientation resulted in high coefficient of thermal expansion in the polymer matrix. In this regard, proper composite design is very crucial in determining the performance of the proposed green hybrid composite tooling.

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3 1.2 Problem Statement

During the manufacturing of aerospace components, tooling used is usually made of carbon fiber or glass fiber reinforced epoxy composite which is difficult to be recycled or disposed. As a green hybrid composite tooling, the incorporation of natural fiber and synthetic fiber in these tooling materials could lead to new venture in tooling industries. Tooling material is subjected to repeated thermal cycling during in service and is likely to induce distortion on the tooling due to the difference in thermal mass and coefficient of thermal expansion between the natural fiber and synthetic fibers. However, no studies have been undertaken to determine thermal history of the natural fiber in composite. Besides, hybrid configuration is also important to achieve optimum result by varying the fiber orientation and the stacking sequence of natural fiber/glass fiber laminae in order to overcome the dimensional instability, low thermal degradation and moisture absorption of hybrid composites associated with natural fibers.

1.3 Objectives

1. To fabricate natural fiber/ glass fiber reinforced epoxy hybrid composite by varying fiber orientation and stacking sequence of natural and glass fiber laminae through hand lay up and vacuum bagging techniques.

2. To characterize the physical, and mechanical behavior of natural fiber/ glass fiber reinforced epoxy hybrid composite in order to establish structure – property relationship.

3. To investigate deformation behavior associated with the dimensional stability of natural fiber/ glass fiber reinforced epoxy hybrid composite subjected to thermal cycling for the application in composite tooling.

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4 1.4 Scope

In this research, jute fiber mat and E-glass fiber mat were used as reinforcement in the epoxy laminate composite. The laminate composite was fabricated through hand lay up and vacuum bagging techniques by varying the stacking sequence of fiber laminae and fiber orientation (0 /90 or 45 /-45 ). Two composite systems encompassed of different laminate layers were produced, that were 7 and 9 plies. For characterization of raw materials, Scanning Electron Microscopy (SEM) is used to determine the fiber morphology. Meanwhile, the physical testing is carried out in terms of the density measurement and water absorption capacity. On the other hand, the dimensional stability of jute/glass fiber reinforced epoxy laminate composite is measured after subjected to 15 cylces of thermal cycling. The thermal cycling is carried out at 1800C for a period of 10 minutes and subsequent cooling at room temperature. From the aspect of mechanical testing, Universal Testing Machine (UTM) is employed to study the flexural behavior of the laminate composite prior and post thermal cycling. The fracture mode of the laminate composite is then analyzed through microscopic observation.

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5 A literature review on previous research work in various areas which is relevant to this research is presented in this chapter.

2.1 Tooling

In manufacturing applications, tooling required to fabricate most composite parts can be subdivided into several major category including ply layup tools, skin or mould forms, curing aids, handling tools, drilling and trimming tools, assembly tools, mould and mandrels (National Aeronautics and Space Administration, NASA, 1990). However, mould which used forming composite part is known as tools. In aerospace industry, mold is widely used during hand lay-up process. According to NASA (1990) cited major factors must be considered in design and fabrication of tooling for structural and mechanical components are:

i. Dimensional tolerance control and configuration stability – low coefficient of thermal expansion (CTE) is required.

ii. Location of part in structural reliable assembly to give the lowest possible cost.

iii. Contour and size of the part. iv. Control the fiber orientation.

LITERATURE REVIEW

CHAPTER 2

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6 v. Other factors: cost, tool service life, heat up rate, total energy

requirements, production rates and related facility costs.

From Lucas and Danford (2009) also had highlighted tooling is critically important where mold tool must be low-cost, rigid and durable and offer a CTE that matches of the composites part. (Stewart, 2010) also had mentioned the tooling must be cost effective, UV resistant, damage to tolerance and able to resist environmental degradation in maintaining the dimensional and stability of tooling. Therefore, long lead times and material availability is also growing concerns with alloy-based tools.

2.1.1 Metallic Tooling

Traditionally, high performance composite parts are formed can be made of metals typically Invar, aluminum or steels. Invar 36 (36% nickel) or Invar 42 (42% nickel) which are well-known metal tooling materials composed low carbon austenite steel alloy with very low CTE (from 0.5 - 6 × 10−6in/in/℉). Invar refers to the metal‟s „invariable‟ dimensional properties. The production of metal tooling can withstand to repeated cycles and maintain good surface finish and dimensional accuracy. Thus, metal tooling such steel can produce high-volume of composite parts because durable and coefficient of thermal expansion which close to that of reinforced plastics used to mould the part (Stewart., 2010). By the way, tools costs and complexity is increased as the part performance requirement and numbers parts to be produced increased. Even metal tool are able to withstand many thousands production cycles, the major drawback of metal tool is relatively heavy when composite manufacturers producing the large scale of composite part.

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2.1.2 Composite Tooling

Due to the excessive weight of metal tooling resulted many manufacturers have turned to composite tooling. Cadden and Sadesky (1998) stated composite mould tooling has several basic advantages. For instance, composite tooling is a low cost because the composite prepreg materials can be laid on plaster model and then cured, the CTE of tooling materials is compatible, and graphite mould tools provide uniform temperature distribution which allows the composite part heated up evenly and prevent internal residual stress. In addition, if damage occurs new tool can be fabricated rapidly and economically from original master model. Table 2.1 provides some properties for most commonly used tooling materials.

Table 2.1: Typical Properties of Tooling Materials (Source: Cadden and Sadesky, 1998). Material Thermal Conductivity, (W/m.K) Coefficient of Thermal Expansion (m/m.K) Apparent Density (g/cm3)

Specific Heat (kJ/kg.K) Thermal Mass (J/g.K)

Graphite 400 1.5 – 2.0 1.78 0.25 0.44

Aluminum 1395 13.0 2.70 0.23 0.062

Steel 350 6.7 7.86 0.11 0.86

Nickel 500 6.6 8.90 0.11 0.98

Carbon-Fiber/ Epoxy

24 – 42 0 – 1.5 1.50 0.25 0.38

Fiberglass/Epoxy 22 – 30 7 – 13 1.9 0.3 0.57 Ceramics (MgO,

� 2 3 Gypsum)

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3 1.2 Problem Statement

1.3 Objectives

2. To characterize the physical, and mechanical behavior of natural fiber/ glass fiber reinforced epoxy hybrid composite in order to establish structure – property relationship.

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4 1.4 Scope

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5 A literature review on previous research work in various areas which is relevant to this research is presented in this chapter.

2.1 Tooling

i. Dimensional tolerance control and configuration stability – low coefficient of thermal expansion (CTE) is required.

ii. Location of part in structural reliable assembly to give the lowest possible cost.

iii. Contour and size of the part. iv. Control the fiber orientation.

LITERATURE REVIEW

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6 v. Other factors: cost, tool service life, heat up rate, total energy

requirements, production rates and related facility costs.

2.1.1 Metallic Tooling

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2.1.2 Composite Tooling

Table 2.1: Typical Properties of Tooling Materials (Source: Cadden and Sadesky, 1998). Material Thermal Conductivity, (W/m.K) Coefficient of Thermal Expansion (m/m.K) Apparent Density (g/cm3)

Specific Heat (kJ/kg.K) Thermal Mass (J/g.K)

Graphite 400 1.5 – 2.0 1.78 0.25 0.44

Aluminum 1395 13.0 2.70 0.23 0.062

Steel 350 6.7 7.86 0.11 0.86

Nickel 500 6.6 8.90 0.11 0.98

Carbon-Fiber/ Epoxy

24 – 42 0 – 1.5 1.50 0.25 0.38

Fiberglass/Epoxy 22 – 30 7 – 13 1.9 0.3 0.57

Ceramics (MgO,

� 2 3 Gypsum)

Thermal Behavior Of Natural Fiber Mat Hybrid Composite For Tooling Materials.

UNIVERSITI TEKNIKAL MALAYSIA MELAKA