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Using DCB and Pull-Out Tests for Experimental Investigation of Rib-Skin Interface Fracture Toughness of Stiffened Composite Shell

  • A. Korjakins
  • O. Ozolins
  • D. Pizele
Conference paper

Abstract

With the increased emphasis on reducing the cost of manufacturing composite structures, secondary bonding or co-curing is an attractive option to eliminate the need for mechanically fastening subassemblies. Many composite components in aerospace structures consist of flat or curved panels with co-cured frames and stiffeners. Out-of plane loading such as internal pressure in a composite fuselage or out-of-plane deformations in a compression loaded post-buckled panel may cause the frame or stiffener to debond from the panel [ 1 ].

Keywords

Progressive Failure Aerospace Structure Secondary Bonding Interface Fracture Toughness Curve Panel 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

References

  1. 1.
    Minguet P. J., Fedro M. J., Brien T. K. O., Martin R. H., Ilcewicz L. B., Awerbuch J. am Wang A., In Proceedings, Fourth NASA/DoD Advanced Composite Technology Conference Salt Lake City, UT, June 1993, 58–65Google Scholar
  2. 2.
    Key C. T., Garnich M. R. and Hansen A. C, Composite Structures, vol. 65, 357–366, 2004CrossRefGoogle Scholar

Copyright information

© Springer 2007

Authors and Affiliations

  • A. Korjakins
    • 1
  • O. Ozolins
    • 1
  • D. Pizele
    • 1
  1. 1.Institute of Materials and StructuresRiga Technical UniversityRigaLatvia

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