Mechanics of Aeronautical Composite Materials [Hardcover]

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.

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.