Experimental evidence indicates that the incorporation of an insert increases the out-of-plane load transfer capability of an integral composite joint [1,2]. The detailed analysis of the integral joint concept has been conducted with linear-elastic finite element techniques for the graphite epoxy material system. Discussion of the finite element model, material properties and strength criteria for the no-insert, titanium insert and graphite-epoxy insert concepts is presented. Correlation with available experimental data shows relatively close agreement with analytical predic tions.
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References
1.
E.B. Maske, et al., "Wing/Inlet Composite Advanced Development," AFFDL-TR-70-88, Air Force Flight Dynamics Laboratory, Wright-Patterson AFB, ( 1976)
2.
J.W. Gillespie, Jr. , "Evaluation of the Embedded Spar Composite Design Concept ," Master's thesis, Department of Mechanical and Aerospace Engineering, University of Delaware, Newark, Delaware , (1978).
