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The Resource Mechanics of aeronautical composite materials, Christopher Bouvet

Mechanics of aeronautical composite materials, Christopher Bouvet

Label
Mechanics of aeronautical composite materials
Title
Mechanics of aeronautical composite materials
Statement of responsibility
Christopher Bouvet
Creator
Subject
Language
eng
Member of
http://library.link/vocab/creatorName
Bouvet, Christophe,
Dewey number
620.1/18
Illustrations
illustrations
Index
index present
Literary form
non fiction
Nature of contents
  • dictionaries
  • bibliography
Series statement
Mechanical engineering and solid mechanics series
http://library.link/vocab/subjectName
  • Laminated materials
  • Aeronautics
Label
Mechanics of aeronautical composite materials, Christopher Bouvet
Instantiates
Publication
Bibliography note
Includes bibliographical references and index
Contents
  • Cover; Half-Title Page; Title Page; Copyright Page; Contents; Foreword; Preface; Introduction; 1. Presentation of an Aeronautical Unidirectional Composite; 1.1. Introduction; 1.2. Carbon/epoxy composite T300/914; 1.3. Polymers; 2. Characteristics of UD Ply; 2.1. State of stress of UD ply; 2.2. Tensile test in the l-direction; 2.3. Tensile test along the t-direction; 2.4. Shear test; 2.5. General case; 3. Characteristics of a UD Ply in a Given Direction; 3.1. Off-axis tensile test; 4. Fracture of a Laminated Composite; 4.1. Fracture of a UD ply; 4.1.1. Longitudinal tension
  • 4.1.2. Longitudinal compression4.1.3. Transverse tension; 4.1.4. Transverse compression; 4.1.5. In-plane shear; 4.2. Fracture of a laminate; 5. Fracture Criteria of a UD Ply; 5.1. Maximum stress fracture criterion; 5.2. Maximum strain fracture criterion; 5.3. Hill's criterion; 5.4. Tsai-Wu criterion; 5.5. Yamada-Sun criterion; 5.6. Conclusion; 6. Membrane Behavior of a Laminated Composite Plate; 6.1. Generalities and notations; 6.2. Membrane behavior, bending behavior and mirror symmetry; 6.3. Resultant forces; 6.4. Displacement field, stress field and strain field
  • 6.5. Tension / shear coupling7. Bending Behavior of a Laminated Composite Plate; 7.1. Notations; 7.2. Resultant moments; 7.3. Displacement field, stress field and strain field; 7.4. Bending/twisting coupling; 8. The Fracture Criterion of a Laminate; 8.1. The sizing criterion; 8.2. Test on a composite structure; 8.3. Sizing principle; 8.4. Sizing a given structure for a given loading; 8.5. Optimal structure for a given load; 9. Damage Tolerance; 9.1. The principle of damage tolerance; 9.2. Damage during impact and compression after impact; 9.3. Sizing for impact damage tolerance
  • 10. Interlaminar and Out-of-Plane Shear Stress10.1. Tension of a cross-ply laminate [0,90]S; 10.2. Tension of a cross-ply laminate [45,-45]S; 10.3. Out-of-plane shear stress; 11. Holed and Bolted Plates; 11.1. Calculating holed composite plates; 11.2. Calculating the multi-bolt composite joints; 12. Buckling; 12.1. Reminder surrounding beam buckling; 12.2. Buckling of plates under compression; 12.3. Plate buckling under shear loading; 13. Miscellaneous Rules for Stacking; 14. Exercises; 14.1. Experimental determination of the characteristics of a UD material; 14.2. Fracture of a laminate
  • 14.3. Shear modulus14.4. Optimization of stacking sequence; 14.5. Composite tube; 14.6. Laminate calculation without calculation; 14.7. Sandwich beam under bending; 14.8. Laminate plate under compression; 14.9. Tube under torsion/internal pressure; 14.10. Optimization of a fabric with a strain fracture criterion; 14.10.1. Part 1: preamble; 14.10.2. Part 2: quasi-isotropic stacking sequence; 14.10.3. Part 3: stacking sequence optimization; 14.10.4. Part 4: stacking sequence optimization under bending; 14.11. Open hole tensile test; 14.12. Multi-bolt composite joint
Control code
on1001454669
Dimensions
unknown
Extent
1 online resource
Form of item
online
Isbn
9781119459057
Other physical details
illustrations (some color)
Specific material designation
remote
System control number
(OCoLC)1001454669
Label
Mechanics of aeronautical composite materials, Christopher Bouvet
Publication
Bibliography note
Includes bibliographical references and index
Contents
  • Cover; Half-Title Page; Title Page; Copyright Page; Contents; Foreword; Preface; Introduction; 1. Presentation of an Aeronautical Unidirectional Composite; 1.1. Introduction; 1.2. Carbon/epoxy composite T300/914; 1.3. Polymers; 2. Characteristics of UD Ply; 2.1. State of stress of UD ply; 2.2. Tensile test in the l-direction; 2.3. Tensile test along the t-direction; 2.4. Shear test; 2.5. General case; 3. Characteristics of a UD Ply in a Given Direction; 3.1. Off-axis tensile test; 4. Fracture of a Laminated Composite; 4.1. Fracture of a UD ply; 4.1.1. Longitudinal tension
  • 4.1.2. Longitudinal compression4.1.3. Transverse tension; 4.1.4. Transverse compression; 4.1.5. In-plane shear; 4.2. Fracture of a laminate; 5. Fracture Criteria of a UD Ply; 5.1. Maximum stress fracture criterion; 5.2. Maximum strain fracture criterion; 5.3. Hill's criterion; 5.4. Tsai-Wu criterion; 5.5. Yamada-Sun criterion; 5.6. Conclusion; 6. Membrane Behavior of a Laminated Composite Plate; 6.1. Generalities and notations; 6.2. Membrane behavior, bending behavior and mirror symmetry; 6.3. Resultant forces; 6.4. Displacement field, stress field and strain field
  • 6.5. Tension / shear coupling7. Bending Behavior of a Laminated Composite Plate; 7.1. Notations; 7.2. Resultant moments; 7.3. Displacement field, stress field and strain field; 7.4. Bending/twisting coupling; 8. The Fracture Criterion of a Laminate; 8.1. The sizing criterion; 8.2. Test on a composite structure; 8.3. Sizing principle; 8.4. Sizing a given structure for a given loading; 8.5. Optimal structure for a given load; 9. Damage Tolerance; 9.1. The principle of damage tolerance; 9.2. Damage during impact and compression after impact; 9.3. Sizing for impact damage tolerance
  • 10. Interlaminar and Out-of-Plane Shear Stress10.1. Tension of a cross-ply laminate [0,90]S; 10.2. Tension of a cross-ply laminate [45,-45]S; 10.3. Out-of-plane shear stress; 11. Holed and Bolted Plates; 11.1. Calculating holed composite plates; 11.2. Calculating the multi-bolt composite joints; 12. Buckling; 12.1. Reminder surrounding beam buckling; 12.2. Buckling of plates under compression; 12.3. Plate buckling under shear loading; 13. Miscellaneous Rules for Stacking; 14. Exercises; 14.1. Experimental determination of the characteristics of a UD material; 14.2. Fracture of a laminate
  • 14.3. Shear modulus14.4. Optimization of stacking sequence; 14.5. Composite tube; 14.6. Laminate calculation without calculation; 14.7. Sandwich beam under bending; 14.8. Laminate plate under compression; 14.9. Tube under torsion/internal pressure; 14.10. Optimization of a fabric with a strain fracture criterion; 14.10.1. Part 1: preamble; 14.10.2. Part 2: quasi-isotropic stacking sequence; 14.10.3. Part 3: stacking sequence optimization; 14.10.4. Part 4: stacking sequence optimization under bending; 14.11. Open hole tensile test; 14.12. Multi-bolt composite joint
Control code
on1001454669
Dimensions
unknown
Extent
1 online resource
Form of item
online
Isbn
9781119459057
Other physical details
illustrations (some color)
Specific material designation
remote
System control number
(OCoLC)1001454669

Library Locations

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