Abstract
For this study, woven glass and carbon fibres reinforced composite materials were produced. Composite materials have been produced with eight laminates. For experimental study, specimens with 10 mm internal hole were prepared. Then, these specimens were repaired by using adhesive and composite patches with different repair parameters. Two different bonding patch type were used for external bonding patch repair of the specimens. These were wet lay out patches and prepreg patches. Test specimens were prepared in necessary curing temperatures and laboratory conditions. By performing the unidirectional tensile test to these specimens, the ultimate failure loads of these repaired specimens were indicated. By comparing these ultimate failure loads of repaired specimens that prepared with various parameters, the effects of several repair parameters on the ultimate failure strength are investigated. These repair parameters are patch bonding area (D/W ratio), bonding length, adhesive thickness and patch thickness.
Highlights
With technological improvements, applications of composite materials have been increased both commercial and military aircraft structures applications in recent years
The ultimate failure loads of the structures repaired with prepreg bonding technique were increased by increasing the patch thickness
For the structure that repaired with W.L. bonding technique, the failure loads have increased gradually to the patch thickness of the 3 plies values and after that, the peeling effect has occurred in repaired structure than, the failure load decrease dramatically
Summary
Applications of composite materials have been increased both commercial and military aircraft structures applications in recent years. 2. Experimental The current work investigated the performance of the external bonded patch repairs under tensile loading by indicating the ultimate failure loads of repaired laminated composite structures. The ultimate failure loads of the structures repaired with prepreg bonding technique were increased by increasing the patch thickness (increase the ply number).
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