Verification of the Combined Load Compression (CLC) Test Method
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Verification of the Combined Load Compression (CLC) Test Method

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  • Creators:
  • Corporate Creators:
    University of Wyoming.
  • Corporate Contributors:
    United States. Federal Aviation Administration. Office of Aviation Research
  • Subject/TRT Terms:
  • Publication/ Report Number:
    DOT/FAA/AR-00/26
  • Resource Type:
    Tech Report
  • Geographical Coverage:
    United States
  • TRIS Online Accession Number:
    00903501
  • Edition:
    Final Report
  • Corporate Publisher:
    University of Wyoming
  • Abstract:
    The determination of lamina compressive strength and modulus using the Combined Loading Compression (CLC) test method developed by the University of Wyoming was investigated. In this test method an untabbed, [90/0]ns cross-ply test coupon is tested in uniaxial compression using the CLC test fixture. The longitudinal modulus and strength of the 0°-plies are determined by applying a back-out factor, calculated using classical lamination theory, to the measured longitudinal laminate modulus and strength. A parametric study revealed that specimen quality, load train alignment, and fixture dimensional tolerances have a large impact on the measured compressive properties. Thus, a significant amount of time was dedicated to developing specimen fabrication and testing procedures to minimize variations in the measured compressive properties. A comparative study of the CLC and Illinois Institute of Technology Research Institute (IITRI) test fixtures showed that results obtained with the CLC test fixture are statistically similar to those obtained from the IITRI test fixture. However, the CLC test fixture is easier to use, less expensive to fabricate, and much less massive than the IITRI test fixture. In a second portion of the comparative study, the 0°-ply compressive strength obtained using [90/0]ns cross-ply test specimens was compared to the 0°-ply compressive strength obtained using quasi-isotropic test specimens. This revealed that the 0°-ply compressive strength was independent of the laminate orientation. This “backed out” 0°-ply compressive strength is then by definition the “design value” for the strength of the unidirectional composite material in compression.
  • Format:
    PDF
  • Funding:
    Grant 94-G-009
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