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Wednesday, April 22, 2020 | History

3 edition of Thermal residual stresses in silicon-carbide/titanium [0/90] laminate found in the catalog.

Thermal residual stresses in silicon-carbide/titanium [0/90] laminate

Thermal residual stresses in silicon-carbide/titanium [0/90] laminate

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Published by National Aeronautics and Space Administration, Langley Research Center, For sale by the National Technical Information Service in Hampton, Va, [Springfield, Va .
Written in English

    Subjects:
  • Laminated materials.,
  • Finite element method.

  • Edition Notes

    StatementC.A. Bigelow.
    SeriesNASA technical memorandum -- 107649., NASA technical memorandum -- 107649.
    ContributionsLangley Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14685611M


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Thermal residual stresses in silicon-carbide/titanium [0/90] laminate Download PDF EPUB FB2

Get this from a library. Thermal residual stresses in silicon-carbide/titanium [0/90] laminate. [C A Bigelow; Langley Research Center.]. The current work formulated a micromechanical analysis of a cross-ply laminate and calculated the thermal residual stress in a very thick (0/90)[sub 2n] silicon-carbide/titanium laminate.

Results were also shown for a unidirectional laminate of the same material. J.F. Durodula, B. DerbyAn analysis of thermal residual stresses in Ti alloy reinforced with SiC and Al 2 O 3 fibres Acta Metall Mater, 42 (5) (), pp.

Google ScholarCited by: 3. Bigelow, C. A., “Thermal Residual Stresses in Silicon-Carbide/Titanium [0/90] Laminate, ” Journal of Composite Technology & Research, 15,– CrossRef Google Scholar [6]Cited by: 1.

Bigelow, C.A. () Thermal residual stresses in a silicon-carbide/titanium [0/90] laminate. ASTM J. Comp. Tech. Res. 15, – Google ScholarCited by: 3. The current work formulated a micromechanical analysis of a cross-ply laminate and calculated the thermal residual stress in a very thick (0/90)(sub 2n) silicon-carbide/titanium laminate.

Working temperature variation effect on the failure envelope of continuous fiber-reinforced composites in a Silicon-Carbide/Titanium [0/90] laminate. of thermal residual stresses in the. Classical laminate theory models for woven fabric composites (Raju, IS and Wang, JT), Oct., Silicon carbide Micromechanical modeling of process- induced residual stresses in TiAI- I INb/SCS-6 composite (Chandra, N, Anantb, CR, and Garmestani, H), Jan., 37 Silicon carbide/titanium.

@article{osti_, title = {Notch sensitivity and stress redistribution in three ceramic-matrix composites}, author = {Mackin, T J and He, M Y and Evans, A G and Purcell, T E}, abstractNote = {Fiber-reinforced ceramic-matrix composites (CMCs) depend upon inelastic mechanisms to diffuse stress concentrations associated with holes, notches, and cracks.

Bigelow, C.A., "Thermal Residual Stresses in a Silicon-Carbide/Titanium [0/90] Laminate." Journal of Composites Technology & Research, 15(4): p. Nicholas, T., R1-R "ASTM E, Standard Guide for Installing Bonded Resistance Strain Gauges," in Annual Book of ASTM Standards. ASME: West Conshohocken, PA.

"ASTM E 5/5(1). This banner text can have markup. web; books; video; audio; software; images; Toggle navigation. laminate shear adhesive load aircraft structures joint ply moisture materials for aircraft structural fatigue mechanical impact loading applications laminates stresses joints thickness analysis systems plies compression pre Material and specimen The material used in this study is a carbon fiber-reinforced epoxy (CF/EP) laminate with a symmetric, quasi-isotropic lay-up of 24 plies [°/0°/45°/90°] 3s.

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