Ultimate Response of Composite Cylinders Under Flexural Load

[+] Author and Article Information
Zheng-Ming Huang

Professor, School of Aeronautics, Astronautics & Mechanics, Tongji University, 1239 Siping Road, Shanghai 200092, People's Republic of China huangzm@mail.tongji.edu.cn

J. Appl. Mech 72(3), 313-321 (Oct 28, 2003) (9 pages) doi:10.1115/1.1867990 History: Received April 21, 2002; Revised October 28, 2003

Composite cylinders are generally used as primary load carrying structures. Their constitutive behavior up to failure is crucial for a critical design. This paper focuses on the ultimate flexural strength of a polymer based composite cylinder subjected to bending. In such a case, the outmost filament of the cylinder subjected to the maximum bending stress fails the first. The complexity, however, lies in the fact that the failure of this outmost filament generally does not correspond to the ultimate failure. Additional loads can still be applied to the cylinder and a progressive failure process will result. To deal with such a problem in this paper, the cylinder is discretized into a number of lamina layers with different widths. The bridging micromechanics model [Huang, Z. M., Composites Part A, 2001] combined with the classical lamination theory has been applied to understand the progressive failure process generated in the cylinder. Only its constituent fiber and matrix properties under bending are necessary for this understanding and reasonably good accuracy has been achieved. However, the ultimate failure of the cylinder cannot be figured out only based on a stress failure criterion, as one cannot know a priori which ply failure corresponds to the ultimate failure. An additional critical deflection (curvature) condition must be employed also. By using both the stress and the deflection conditions, the estimated ultimate strength of the cylinder agreed well with an experimental measurement.

Copyright © 2005 by American Society of Mechanical Engineers
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Figure 4

An elastic–plastic stress–strain curve together with definition of material parameters

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Figure 3

Schematic of the bridging model for a UD lamina

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Figure 2

Analysis of a lamina layer taken from the cylinder

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Figure 1

A composite cylinder consisting of multilayers of laminas

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Figure 5

Measured and predicted load-deflections of a composite cylinder (d=0.5mm and Vf=0.45)

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Figure 6

Load-deflection of R50/H64 pure matrix material under 4-point bending

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Figure 7

Stress–strain data of R50/H64 pure matrix under 4-point bending (not complete due to limitation in the strain gauge measurement range)

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Figure 8

Stress–strain responses of R50/H64 under uniaxial loads

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Figure 9

Comparison between the predicted results of different lamina layers used in discretizing the cross-section of the composite cylinder (d=0.5mm & Vf=0.45)

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Figure 10

Bending modulus of GF/R50 composite cylinder versus fiber volume fraction

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Figure 11

Strength of GF/R50 composite cylinder versus fiber volume fraction under bending



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