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Mechanics of Aeronautical Composite Materials


Mechanics of Aeronautical Composite Materials


1. Aufl.

von: Christophe Bouvet

139,99 €

Verlag: Wiley
Format: PDF
Veröffentl.: 14.08.2017
ISBN/EAN: 9781119459033
Sprache: englisch
Anzahl Seiten: 318

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Beschreibungen

<p>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.</p> <p>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. </p> <p>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.</p> <p>The book also contains corrected exercises for the reader to test their understanding of the different topics covered.</p>
<p>Foreword ix</p> <p>Preface xi</p> <p>Introduction xiii</p> <p><b>Chapter 1 Presentation of an Aeronautical Unidirectional Composite 1</b></p> <p>1.1 Introduction 1</p> <p>1.2 Carbon/epoxy composite T300/914 2</p> <p>1.3 Polymers 5</p> <p><b>Chapter 2 Characteristics of UD Ply 15</b></p> <p>2.1 State of stress of UD ply 15</p> <p>2.2 Tensile test in the l-direction 16</p> <p>2.3 Tensile test along the t-direction 17</p> <p>2.4 Shear test 19</p> <p>2.5 General case 20</p> <p><b>Chapter 3 Characteristics of a UD Ply in a Given Direction 27</b></p> <p>3.1 Off-axis tensile test 27</p> <p><b>Chapter 4 Fracture of a Laminated Composite 37</b></p> <p>4.1 Fracture of a UD ply 37</p> <p>4.1.1 Longitudinal tension 37</p> <p>4.1.2 Longitudinal compression 40</p> <p>4.1.3 Transverse tension 42</p> <p>4.1.4 Transverse compression 43</p> <p>4.1.5 In-plane shear 44</p> <p>4.2 Fracture of a laminate 46</p> <p><b>Chapter 5 Fracture Criteria of a UD Ply 49</b></p> <p>5.1 Maximum stress fracture criterion 50</p> <p>5.2 Maximum strain fracture criterion 54</p> <p>5.3 Hill’s criterion 58</p> <p>5.4 Tsai–Wu criterion 65</p> <p>5.5 Yamada–Sun criterion 70</p> <p>5.6 Conclusion 71</p> <p><b>Chapter 6 Membrane Behavior of a Laminated Composite Plate 73</b></p> <p>6.1 Generalities and notations 73</p> <p>6.2 Membrane behavior, bending behavior and mirror symmetry 75</p> <p>6.3 Resultant forces 78</p> <p>6.4 Displacement field, stress field and strain field 80</p> <p>6.5 Tension / shear coupling 83</p> <p><b>Chapter 7 Bending Behavior of a Laminated Composite Plate 97</b></p> <p>7.1 Notations 97</p> <p>7.2 Resultant moments 97</p> <p>7.3 Displacement field, stress field and strain field 99</p> <p>7.4 Bending/twisting coupling 105</p> <p><b>Chapter 8 The Fracture Criterion of a Laminate 115</b></p> <p>8.1 The sizing criterion 115</p> <p>8.2 Test on a composite structure 117</p> <p>8.3 Sizing principle 119</p> <p>8.4 Sizing a given structure for a given loading 119</p> <p>8.5 Optimal structure for a given load 131</p> <p><b>Chapter 9 Damage Tolerance 139</b></p> <p>9.1 The principle of damage tolerance 139</p> <p>9.2 Damage during impact and compression after impact 144</p> <p>9.3 Sizing for impact damage tolerance 148</p> <p><b>Chapter 10 Interlaminar and Out-of-Plane Shear Stress 151</b></p> <p>10.1 Tension of a cross-ply laminate [0,90]s 151</p> <p>10.2 Tension of a cross-ply laminate [45,–45]s 153</p> <p>10.3 Out-of-plane shear stress 154</p> <p><b>Chapter 11 Holed and Bolted Plates 157</b></p> <p>11.1 Calculating holed composite plates 157</p> <p>11.2 Calculating the multi-bolt composite joints 167</p> <p><b>Chapter 12 Buckling 179</b></p> <p>12.1 Reminder surrounding beam buckling 179</p> <p>12.2 Buckling of plates under compression 180</p> <p>12.3 Plate buckling under shear loading 186</p> <p><b>Chapter 13 Miscellaneous Rules for Stacking 189</b></p> <p><b>Chapter 14 Exercises 191</b></p> <p>14.1 Experimental determination of the characteristics of a UD material 191</p> <p>14.2 Fracture of a laminate 193</p> <p>14.3 Shear modulus 194</p> <p>14.4 Optimization of stacking sequence 195</p> <p>14.5 Composite tube 195</p> <p>14.6 Laminate calculation without calculation 196</p> <p>14.7 Sandwich beam under bending 197</p> <p>14.8 Laminate plate under compression 200</p> <p>14.9 Tube under torsion/internal pressure 203</p> <p>14.10 Optimization of a fabric with a strain fracture criterion 204</p> <p>14.10.1 Part 1: preamble 204</p> <p>14.10.2 Part 2: quasi-isotropic stacking sequence 205</p> <p>14.10.3 Part 3: stacking sequence optimization 206</p> <p>14.10.4 Part 4: stacking sequence optimization under bending 206</p> <p>14.11 Open hole tensile test 206</p> <p>14.12 Multi-bolt composite joint 209</p> <p><b>Chapter 15 Solutions to the Exercises 211</b></p> <p>15.1 Experimental determination of the characteristics of a UD material 211</p> <p>15.2 Fracture of a laminate 219</p> <p>15.3 Shear modulus 225</p> <p>15.4 Optimization of stacking sequence 229</p> <p>15.5 Composite tube 233</p> <p>15.6 Laminate calculation without calculation 240</p> <p>15.7 Sandwich beam under bending 242</p> <p>15.8 Laminate plate under compression 253</p> <p>15.9 Tube under torsion/internal pressure 263</p> <p>15.10 Optimization of a fabric with a strain fracture criterion 266</p> <p>15.11 Open hole tensile test 276</p> <p>15.12 Multi-bolt composite joint 280</p> <p>Bibliography 289</p> <p>Index 293</p>
Review copy sent to The Aeronautical Journal 23/11/2017. 
<b>Christophe Bouvet</b>, ISAE-SUPAÉRO, France.

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