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a preliminary damage tolerance methodology for composite structuresThe 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.
Document ID
19830025688
Document Type
Conference Paper
Authors
Wilkins, D. J.
(General Dynamics Corp. Fort Worth, TX, United States)
Date Acquired
August 11, 2013
Publication Date
August 1, 1983
Publication Information
Publication: NASA. Langley Research Center Failure Anal. and Mech. of Failure of Fibrous Composite Struct.
Subject Category
COMPOSITE MATERIALS
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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