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Improvements in mechanical properties of a carbon

碳纤维文献(英文)

Article Outline

1.

Introduction

2.

Materials, fabrication and experimental procedures

2.1. Materials

2.2. Composite laminate fabrication

2.3. Specimen configurations and test procedures

3.

Results and discussions

3.1. Tensile strength and stiffness

3.2. Tension–tension cycling at R = +0.1

3.3. Tension–compression cycling at R = 0.1

4.

Summary and conclusions

Acknowledgements

References

1. Introduction

The newest commercial aircraft designs propose a reduction in weight by having over 50% of the primary structural components fabricated with epoxy based carbon fibers or carbon-glass fiber hybrid reinforced composites [1] and [2]. Using advanced light weight and high strength composites is necessary in order to achieve the reduced fuel consumption and improved passenger comfort goals of these future commercial aircraft design innovations. Fiber reinforced epoxy composite laminates are known to have high in-plane stiffness, strength and fatigue resistance under tensile loadings. The fibers have the primary role to carry the load imposed on the composite laminate. Carbon fibers have an exceptional tensile strength, but they have essentially no compressive load carrying capability [3]. The role of the matrix is to provide bulk to the composite laminate and transfer load between fibers. However, the epoxy matrix can be brittle with poor strength and toughness. There is a third constituent in composite laminates, the fiber/fabric-matrix interfaces. A weak fiber/fabric-matrix interfacial strength in composite laminates could be

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