Mechanics of Aircraft Structures / Edition 2

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Mechanics of Aircraft Structures, Second Edition is the revised update of the original bestselling textbook about aerospace engineering. This book covers the materials and analysis tools used for aircraft structural design and mechanics in the same easy to understand manner. The new edition focuses on three levels of coverage driven by recent advances in industry: the increase in the use of commercial finite element codes require an improved capability in students to formulate the problem and develop a judgement of the accuracy of the numerical results; the focus on fracture mechanics as a tool in studying damage tolerance and durability has made it necessary to introduce students at the undergraduate level to this subject; a new class of materials including advanced composites, are very different from the traditional metallic materials, requiring students and practitioners to understand the advantages the new materials make possible. This new edition will provide more homework problems for each chapter, more examples, and more details in some of the derivations.

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Product Details

  • ISBN-13: 9780471699668
  • Publisher: Wiley
  • Publication date: 4/28/2006
  • Edition description: REV
  • Edition number: 2
  • Pages: 320
  • Sales rank: 766,781
  • Product dimensions: 6.56 (w) x 9.29 (h) x 0.84 (d)

Meet the Author

C. T. SUN, PHD, is the Neil A. Armstrong Distinguished Professor inthe School of Aeronautics and Astronautics at Purdue University in West Lafayette, Indiana, and the recipient of the 2004 Purdue University Research Award. Dr. Sun teaches composites, elasticity, fracture mechanics, and aircraft structures. He is a Fellow of both the American Institute of Aeronautics and Astronautics (AIAA), the American Society of Mechanical Engineers (ASME), and the American Society for Composites (ASC).

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Table of Contents


Preface to the First Edition.

1 Characteristics of Aircraft Structures andMaterials.

1.1 Introduction.

1.2 Basic Structural Elements in Aircraft Structure.

1.2.1 Axial Member.

1.2.2 Shear Panel.

1.2.3 Bending Member (Beam).

1.2.4 Torsion Member.

1.3 Wing and Fuselage.

1.3.1 Load Transfer.

1.3.2 Wing Structure.

1.3.3 Fuselage.

1.4 Aircraft Materials.


2 Introduction to Elasticity.

2.1 Concept of Displacement.

2.2 Strain.

2.3 Stress.

2.4 Equations of Equilibrium in a Nonuniform Stress Field.

2.5 Principal Stress.

2.6 Shear Stress.

2.7 Revisit of Transformation of Stress.

2.8 Linear Stress-Strain Relations.

2.8.1 Strains Induced by Normal Stress.

2.8.2 Strains Induced by Shear Stress.

2.8.3 Three-Dimensional Stress-Strain Relations.

2.9 Elastic Strain Energy.

2.10 Plane Elasticity.

2.10.1 Stress-Strain Relations for Plane Isotropic Solids.

2.10.2 Stress-Strain Relations for Orthotropic Solids in PlaneStress.

2.10.3 Governing Equations.

2.10.4 Solution by Airy Stress Function for Plane IsotropicSolids.


3 Torsion.

3.1 Saint-Venant’s Principle.

3.2 Torsion of Uniform Bars.

3.3 Bars with Circular Cross-Sections.

3.4 Bars with Narrow Rectangular Cross-Sections.

3.5 Closed Single-Cell Thin-Walled Sections.

3.6 Multicell Thin-Walled Sections.

3.7 Warping in Open Thin-Walled Sections.

3.8 Warping in Closed Thin-Walled Sections.

3.9 Effect of End Constraints.


4 Bending and Flexural Shear.

4.1 Derivation of the Simple (Bernoulli–Euler) BeamEquation.

4.2 Bidirectional Bending.

4.3 Transverse Shear Stress due to Transverse Force in SymmetricSections.

4.3.1 Narrow Rectangular Cross-Section.

4.3.2 General Symmetric Sections.

4.3.3 Thin-Walled Sections.

4.3.4 Shear Deformation in Thin-Walled Sections.

4.4 Timoshenko Beam Theory.

4.5 Shear Lag.


5 Flexural Shear Flow in Thin-Walled Sections.

5.1 Flexural Shear Flow in Open Thin-Walled Sections.

5.1.1 Symmetric Thin-Walled Sections.

5.1.2 Unsymmetric Thin-Walled Sections.

5.1.3 Multiple Shear Flow Junctions.

5.1.4 Selection of Shear Flow Contour.

5.2 Shear Center in Open Sections.

5.3 Closed Thin-Walled Sections and Combined Flexural andTorsional Shear Flow.

5.3.1 Shear Center.

5.3.2 Statically Determinate Shear Flow.

5.4 Closed Multicell Sections.


6 Failure Criteria for Isotropic Materials.

6.1 Strength Criteria for Brittle Materials.

6.1.1 Maximum Principal Stress Criterion.

6.1.2 Coulomb–Mohr Criterion.

6.2 Yield Criteria for Ductile Materials.

6.2.1 Maximum Shear Stress Criterion (Tresca Yield Criterion) inPlane Stress.

6.2.2 Maximum Distortion Energy Criterion (von Mises YieldCriterion).

6.3 Fracture Mechanics.

6.3.1 Stress Concentration.

6.3.2 Concept of Cracks and Strain Energy Release Rate.

6.3.3 Fracture Criterion.

6.4 Stress Intensity Factor.

6.4.1 Symmetric Loading (Mode I Fracture).

6.4.2 Antisymmetric Loading (Mode II Fracture).

6.4.3 Relation between K and G.

6.4.4 Mixed Mode Fracture.

6.5 Effect of Crack Tip Plasticity.

6.6 Fatigue Failure.

6.6.1 Constant Stress Amplitude.

6.6.2 SN Curves.

6.6.3 Variable Amplitude Loading.

6.7 Fatigue Crack Growth.


7 Elastic Buckling.

7.1 Eccentrically Loaded Beam-Column.

7.2 Elastic Buckling of Straight Bars.

7.2.1 Pinned–Pinned Bar.

7.2.2 Clamped–Free Bar.

7.2.3 Clamped–Pinned Bar.

7.2.4 Clamped–Clamped Bar.

7.2.5 Effective Length of Buckling.

7.3 Initial Imperfection.

7.4 Postbuckling Behavior.

7.5 Bar of Unsymmetric Section.

7.6 Torsional–Flexural Buckling of Thin-Walled Bars.

7.6.1 Nonuniform Torsion.

7.6.2 Torsional Buckling of Doubly Symmetric Section.

7.6.3 Torsional–Flexural Buckling.

7.7 Elastic Buckling of Flat Plates.

7.7.1 Governing Equation for Flat Plates.

7.7.2 Cylindrical Bending.

7.7.3 Buckling of Rectangular Plates.

7.7.4 Buckling under Shearing Stresses.

7.8 Local Buckling of Open Sections.


8 Analysis of Composite Laminates.

8.1 Plane Stress Equations for Composite Lamina.

8.2 Off-Axis Loading.

8.3 Notation for Stacking Sequence in Laminates.

8.4 Symmetric Laminate under In-Plane Loading.

8.5 Effective Moduli for Symmetric Laminates.

8.6 Laminar Stresses.

8.7 [±45◦] Laminate.



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