Thoughts on the scatter seen in cyclic Mode I fatigue delamination growth in DCB tests

Author:

Mujtaba A.,Stelzer S.,Brunner A.J.,Jones R.

Funder

NASA Langley

Publisher

Elsevier BV

Subject

Civil and Structural Engineering,Ceramics and Composites

Reference26 articles.

1. Federal Aviation Authority. (2009) Airworthiness Advisory Circular No: 20-107B. Composite Aircraft Structure; 09/08/2009.

2. Aviation Investigation Report A05F0047. Loss Of Rudder In Flight Air TRANSAT AIRBUS A310–308 C-GPAT, Miami, Florida, 90 nm S, 06 March 2005. Transportation Safety Board, Canada; Available online at: www.tsb.gc.ca/eng/rapports-reports/aviation/2005/a05f0047/a05f0047.pdf.

3. Baker AA. Structural Health Monitoring of a Bonded Composite Patch Repair on a Fatigue-Cracked F-111C Wing. Defence Science and Technology Organisation, DSTO-RR-0335; 2008.

4. Mode I, II and Mixed Mode I/II delamination growth in composites;Jones;Compos Struct,2014

5. Characterization of Mode I and Mode II delamination growth and thresholds in AS4/PEEK composites;Martin;ASTM STP,1990

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