Using DCB and Pull-Out Tests for Experimental Investigation of Rib-Skin Interface Fracture Toughness of Stiffened Composite Shell
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 ].
KeywordsProgressive Failure Aerospace Structure Secondary Bonding Interface Fracture Toughness Curve Panel
- 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