Comparison of Repair Methods for Cracked Titanium Alloy Aircraft Structures with Single-Sided Adhesively Bonded Composite Patches
نویسندگان
چکیده
Composite patches are widely accepted as a useful practice for the repair of cracked aircraft components and method is vital importance to final performance repaired structures. The present research experimentally studied efficiency processing stability pre-cured, prepreg (including unidirectional plain weave prepregs) wet-layup methods use on Ti-alloy panels through configuration butt joint bonded with one-sided composite patch. these were elaborately evaluated compared via load bearing behavior, microstructure bonding interface, structural failure morphology two batches testing specimens. Typical patterns found in load-displacement curves where initial damage ultimate points divided them into elastic-linear, propagation complete fracture phases. Although co-cure process both can form jigsaw-like demarcation interface between adhesive layer patch achieve good force high recovery loading performance, latter presents porous coefficient variation load-carrying capacity. Conversely, pre-cured laminate failed restore mechanical properties owing weak low axial strength, respectively. was proven be optimal metallic structures when balancing stability.
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ژورنال
عنوان ژورنال: Materials
سال: 2023
ISSN: ['1996-1944']
DOI: https://doi.org/10.3390/ma16196361