Mechanics of Aeronautical Composite Materials

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

• Foreword ixPreface xiIntroduction xiiiChapter 1 Presentation of an Aeronautical Unidirectional Composite 11.1 Introduction 11.2 Carbon/epoxy composite T300/914 21.3 Polymers 5Chapter 2 Characteristics of UD Ply 152.1 State of stress of UD ply 152.2 Tensile test in the l-direction 162.3 Tensile test along the t-direction 172.4 Shear test 192.5 General case 20Chapter 3 Characteristics of a UD Ply in a Given Direction 273.1 Off-axis tensile test 27Chapter 4 Fracture of a Laminated Composite 374.1 Fracture of a UD ply 374.1.1 Longitudinal tension 374.1.2 Longitudinal compression 404.1.3 Transverse tension 424.1.4 Transverse compression 434.1.5 In-plane shear 444.2 Fracture of a laminate 46Chapter 5 Fracture Criteria of a UD Ply 495.1 Maximum stress fracture criterion 505.2 Maximum strain fracture criterion 545.3 Hill’s criterion 585.4 Tsai–Wu criterion 655.5 Yamada–Sun criterion 705.6 Conclusion 71Chapter 6 Membrane Behavior of a Laminated Composite Plate 736.1 Generalities and notations 736.2 Membrane behavior, bending behavior and mirror symmetry 756.3 Resultant forces 786.4 Displacement field, stress field and strain field 806.5 Tension / shear coupling 83Chapter 7 Bending Behavior of a Laminated Composite Plate 977.1 Notations 977.2 Resultant moments 977.3 Displacement field, stress field and strain field 997.4 Bending/twisting coupling 105Chapter 8 The Fracture Criterion of a Laminate 1158.1 The sizing criterion 1158.2 Test on a composite structure 1178.3 Sizing principle 1198.4 Sizing a given structure for a given loading 1198.5 Optimal structure for a given load 131Chapter 9 Damage Tolerance 1399.1 The principle of damage tolerance 1399.2 Damage during impact and compression after impact 1449.3 Sizing for impact damage tolerance 148Chapter 10 Interlaminar and Out-of-Plane Shear Stress 15110.1 Tension of a cross-ply laminate [0,90]s 15110.2 Tension of a cross-ply laminate [45,–45]s 15310.3 Out-of-plane shear stress 154Chapter 11 Holed and Bolted Plates 15711.1 Calculating holed composite plates 15711.2 Calculating the multi-bolt composite joints 167Chapter 12 Buckling 17912.1 Reminder surrounding beam buckling 17912.2 Buckling of plates under compression 18012.3 Plate buckling under shear loading 186Chapter 13 Miscellaneous Rules for Stacking 189Chapter 14 Exercises 19114.1 Experimental determination of the characteristics of a UD material 19114.2 Fracture of a laminate 19314.3 Shear modulus 19414.4 Optimization of stacking sequence 19514.5 Composite tube 19514.6 Laminate calculation without calculation 19614.7 Sandwich beam under bending 19714.8 Laminate plate under compression 20014.9 Tube under torsion/internal pressure 20314.10 Optimization of a fabric with a strain fracture criterion 20414.10.1 Part 1: preamble 20414.10.2 Part 2: quasi-isotropic stacking sequence 20514.10.3 Part 3: stacking sequence optimization 20614.10.4 Part 4: stacking sequence optimization under bending 20614.11 Open hole tensile test 20614.12 Multi-bolt composite joint 209Chapter 15 Solutions to the Exercises 21115.1 Experimental determination of the characteristics of a UD material 21115.2 Fracture of a laminate 21915.3 Shear modulus 22515.4 Optimization of stacking sequence 22915.5 Composite tube 23315.6 Laminate calculation without calculation 24015.7 Sandwich beam under bending 24215.8 Laminate plate under compression 25315.9 Tube under torsion/internal pressure 26315.10 Optimization of a fabric with a strain fracture criterion 26615.11 Open hole tensile test 27615.12 Multi-bolt composite joint 280Bibliography 289Index 293