A Unique and Rational Applications Methodology for Fiber Composite Laminates

[+] Author and Article Information
Richard M. Christensen

Professor Research Emeritus,
Aeronautics and Astronautics Department,
Stanford University,
Stanford, CA 94305
e-mail: christensen@stanford.edu

Contributed by the Applied Mechanics Division of ASME for publication in the JOURNAL OF APPLIED MECHANICS. Manuscript received July 19, 2017; final manuscript received July 21, 2017; published online August 21, 2017. Editor: Yonggang Huang.

ASME doi:10.1115/1.4037412 History: Received July 19, 2017; Revised July 21, 2017

An applications methodology is synthesized from the research-based development of failure theory for orthotropic fiber composite laminates. In effect, this work continues and completes the work of Christensen (2017, “Lamination Theory for the Strength of Fiber Composite Materials,” ASME J. Appl. Mech., 84(7), p. 071007). This failure theory applies for the condition of fiber-dominated behavior, appropriate to carbon fiber—polymeric matrix composites and such similar systems. A lamination theory for stiffness and a separate lamination theory for strength are the outcomes derived here. Final forms are given for 0, 90, ± 45 type orthotropic laminates, with the four lamina orientation volume fractions to be specified in any particular application of interest. Many examples are given of using the new methodology in specific design cases.

Copyright © 2017 by ASME
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Grahic Jump Location
Fig. 1

Coordinate system and fiber orientations in the laminate

Grahic Jump Location
Fig. 2

Failure envelopes for three separate laminates from the same tow material, σ12 = 0




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