Mechanics of Aeronautical Composite Materials
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Mechanics of Aeronautical Composite Materials

Mechanics of Aeronautical Composite Materials


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About the Book

This book presents the principles of composite laminate sizing widely used for composite structures. The focus is on aeronautics in particular, including the concepts of limit loads and ultimate loads. After a brief overview of the main composite materials used in aeronautics, the basic theory of laminated plates and the associated rupture criteria are given. The author presents two fundamental cases of the sizing of aeronautical composite structures: the calculation of the holed structures and their subsequent multi-bolt joints, and the calculation of the buckling. The concept of damage tolerance is also explored, with a focus on its application for tolerance to impact damage. These notions are fundamental for understanding the specificities of the sizing of aeronautical composite structures. The book also contains corrected exercises for the reader to test their understanding of the different topics covered.

Table of Contents:
Foreword ix Preface xi Introduction xiii Chapter 1 Presentation of an Aeronautical Unidirectional Composite 1 1.1 Introduction 1 1.2 Carbon/epoxy composite T300/914 2 1.3 Polymers 5 Chapter 2 Characteristics of UD Ply 15 2.1 State of stress of UD ply 15 2.2 Tensile test in the l-direction 16 2.3 Tensile test along the t-direction 17 2.4 Shear test 19 2.5 General case 20 Chapter 3 Characteristics of a UD Ply in a Given Direction 27 3.1 Off-axis tensile test 27 Chapter 4 Fracture of a Laminated Composite 37 4.1 Fracture of a UD ply 37 4.1.1 Longitudinal tension 37 4.1.2 Longitudinal compression 40 4.1.3 Transverse tension 42 4.1.4 Transverse compression 43 4.1.5 In-plane shear 44 4.2 Fracture of a laminate 46 Chapter 5 Fracture Criteria of a UD Ply 49 5.1 Maximum stress fracture criterion 50 5.2 Maximum strain fracture criterion 54 5.3 Hill’s criterion 58 5.4 Tsai–Wu criterion 65 5.5 Yamada–Sun criterion 70 5.6 Conclusion 71 Chapter 6 Membrane Behavior of a Laminated Composite Plate 73 6.1 Generalities and notations 73 6.2 Membrane behavior, bending behavior and mirror symmetry 75 6.3 Resultant forces 78 6.4 Displacement field, stress field and strain field 80 6.5 Tension / shear coupling 83 Chapter 7 Bending Behavior of a Laminated Composite Plate 97 7.1 Notations 97 7.2 Resultant moments 97 7.3 Displacement field, stress field and strain field 99 7.4 Bending/twisting coupling 105 Chapter 8 The Fracture Criterion of a Laminate 115 8.1 The sizing criterion 115 8.2 Test on a composite structure 117 8.3 Sizing principle 119 8.4 Sizing a given structure for a given loading 119 8.5 Optimal structure for a given load 131 Chapter 9 Damage Tolerance 139 9.1 The principle of damage tolerance 139 9.2 Damage during impact and compression after impact 144 9.3 Sizing for impact damage tolerance 148 Chapter 10 Interlaminar and Out-of-Plane Shear Stress 151 10.1 Tension of a cross-ply laminate [0,90]s 151 10.2 Tension of a cross-ply laminate [45,–45]s 153 10.3 Out-of-plane shear stress 154 Chapter 11 Holed and Bolted Plates 157 11.1 Calculating holed composite plates 157 11.2 Calculating the multi-bolt composite joints 167 Chapter 12 Buckling 179 12.1 Reminder surrounding beam buckling 179 12.2 Buckling of plates under compression 180 12.3 Plate buckling under shear loading 186 Chapter 13 Miscellaneous Rules for Stacking 189 Chapter 14 Exercises 191 14.1 Experimental determination of the characteristics of a UD material 191 14.2 Fracture of a laminate 193 14.3 Shear modulus 194 14.4 Optimization of stacking sequence 195 14.5 Composite tube 195 14.6 Laminate calculation without calculation 196 14.7 Sandwich beam under bending 197 14.8 Laminate plate under compression 200 14.9 Tube under torsion/internal pressure 203 14.10 Optimization of a fabric with a strain fracture criterion 204 14.10.1 Part 1: preamble 204 14.10.2 Part 2: quasi-isotropic stacking sequence 205 14.10.3 Part 3: stacking sequence optimization 206 14.10.4 Part 4: stacking sequence optimization under bending 206 14.11 Open hole tensile test 206 14.12 Multi-bolt composite joint 209 Chapter 15 Solutions to the Exercises 211 15.1 Experimental determination of the characteristics of a UD material 211 15.2 Fracture of a laminate 219 15.3 Shear modulus 225 15.4 Optimization of stacking sequence 229 15.5 Composite tube 233 15.6 Laminate calculation without calculation 240 15.7 Sandwich beam under bending 242 15.8 Laminate plate under compression 253 15.9 Tube under torsion/internal pressure 263 15.10 Optimization of a fabric with a strain fracture criterion 266 15.11 Open hole tensile test 276 15.12 Multi-bolt composite joint 280 Bibliography 289 Index 293

About the Author :
Christophe Bouvet is Professor of Structural Mechanics at the ISAE-SUPAÉRO in France. His research focuses on the sizing and damage of composite structures at the Institut Clément Adler (ICA) in Toulouse, France.

Review :
Review copy sent to The Aeronautical Journal 23/11/2017. 


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Product Details
  • ISBN-13: 9781786301147
  • Publisher: ISTE Ltd and John Wiley & Sons Inc
  • Publisher Imprint: ISTE Ltd and John Wiley & Sons Inc
  • Height: 239 mm
  • No of Pages: 318
  • Returnable: N
  • Weight: 675 gr
  • ISBN-10: 1786301148
  • Publisher Date: 11 Aug 2017
  • Binding: Hardback
  • Language: English
  • Returnable: N
  • Spine Width: 25 mm
  • Width: 163 mm


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