Abstract
The use of composite patching to reinforce aircraft structure is on the increase as it offers advantages over those of rivet fastened metal patches in application. The objective of this research is to determine the thermal residual strains in graphite/epoxy composites on Al-2024 T3 substrate. To realize this, four specimens were produced, of which one was instrumented by bonding several strain gauges on the patch and Al-substrate. Thermal and thermal residual strains were measured as a function of operating temperatures via those gauges.
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