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Record Details

Record 77 of 24989
Delamination, durability and damage tolerance of laminated composite materials
Author and Affiliation:
O'Brien, T. K.(NASA Langley Research Center, U.S. Army, Aerostructures Directorate, Hampton)
Abstract: Research exploring the role of delamination on the durability and damage tolerance of advanced composite materials is reviewed. Recent studies on the characterization of composite delamination are summarized. Recent analytical solutions for interlaminar stresses and strain energy release rates associated with common sources of delamination are also reviewed. The role of delamination in low velocity impact, residual compression strength, and in fatigue is highlighted. Delamination is shown to be the common damage mode observed in all of these problems. A Damage Threshold/Fail-safety concept for addressing composite damage tolerance is discussed.
Publication Date: Jan 01, 1991
Document ID:
19920050146
(Acquired Nov 22, 1995)
Accession Number: 92A32770
Subject Category: STRUCTURAL MECHANICS
Document Type: Conference Paper
Publication Information: (SEE A92-32535)
Publisher Information: United States
Meeting Information: International Conference on Composite Materials (ICCM/8); 8th; July 15-19, 1991; Honolulu, HI; United States
Meeting Sponsor: SAMPE;
AIME;
American Society of Composites
Financial Sponsor: NASA; United States
Organization Source: NASA Langley Research Center; Hampton, VA, United States
Description: 13p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: DAMAGE ASSESSMENT; DELAMINATING; DURABILITY; LAMINATES; TOLERANCES (MECHANICS); COMPRESSIVE STRENGTH; CYCLIC LOADS; FAIL-SAFE SYSTEMS; FATIGUE (MATERIALS); IMPACT DAMAGE; NOTCH STRENGTH
Imprint And Other Notes: IN: Composites; Proceedings of the 8th International Conference on Composite Materials (ICCM/8), Honolulu, HI, July 15-19, 1991. Section 22-29 (A92-32535 13-39). Covina, CA, Society for the Advancement of Material and Process Engineering, 1991, p. 28-A-1 to 28-A-13.
Availability Source: Other Sources
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