Composite Materials for Aircraft Structures, Second Edition - download pdf or read online

By A. Baker, S. Dutton, D. Kelly

ISBN-10: 1563475405

ISBN-13: 9781563475405

Providing an creation to the expertise of composite fabrics as utilized in aeronautical layout and constitution, this article discusses ameliorations among composites and metals, structural layout approaches and in-service functionality of these fabrics.

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Extra info for Composite Materials for Aircraft Structures, Second Edition (Aiaa Education Series)

Example text

In some cases, 7 the composite may become notch-sensitive when a >> 8, the ineffective length, because the strain concentration in the matrix may then lead to fiber fractures at the crack tip. The crack would then become more effective with increasing a, as required in fracture mechanics considerations. 18c. This situation, which occurs in more weakly bonded composites, results in complete notch-insensitivity (failure at the net section strength). 20, taken from Ref. 11. The conditions for crack turning or splitting can be approached from energy considerations.

1 51 Models for Contributions to Work of Fracture for a Discontinuous Fiber Composite, Taken from Ref. 11 II I ^ ~ I ^ 1 l*luuci "y Pull-out (short fibers of length L) Vfo~f82 -~ (L > 28) Vf°'~fL2(L< 2a) 248 Vf( o~f)2y 4Ef Vf(o~f)28 < 3Ef 2Vfr(~ff) 3 (1 - vf)(1 - 2vf) X "fiEf 12(1 - vf) (1 - Vf) 2 aurarx Debonding Stress relaxation - Crack bridging Matrix plastic deformation x vl ~m U where tr is the applied stress and 2a the crack length. 34) which is the familiar Griffith equation. 13 A relationship between G and K can also be obtained for a fiber composite material by modelling it as a continuous linear orthotropic material with the crack propagating on one of the planes of symmetry.

The fibers are left spanning or bridging fatigue cracks if they develop in the aluminum sheets, vastly reducing the rate of crack growth. Taken from Ref. 13. stresses and the favorable residual strength that is produced, ARALL may be pre-stretched. This also overcomes, at a cost, the adverse residual stresses arising from the differences in thermal expansion coefficient between aramid, or glass, and aluminum. GLARE does not require pre-stretching as the high-strain glass fiber used is less susceptible to compressive stresses.

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Composite Materials for Aircraft Structures, Second Edition (Aiaa Education Series) by A. Baker, S. Dutton, D. Kelly


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