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    A preliminary damage tolerance methodology for composite structures (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The certification experience for the primary, safety-of-flight composite structure applications on the F-16 is discussed. The rationale for the selection of delamination as the major issue for damage tolerance is discussed, as well as the modeling approach selected. The development of the necessary coupon-level data base is briefly summarized. The major emphasis is on the description of a full-scale fatigue test where delamination growth was obtained to demonstrate the validity of the selected approach. A summary is used to review the generic features of the methodology.
    Keywords: COMPOSITE MATERIALS
    Type: NASA. Langley Research Center Failure Anal. and Mech. of Failure of Fibrous Composite Struct.; p 67-94
    Format: application/pdf
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