Karbon/epoksi ve E-cam/epoksi ile Onarılmış Çentikli Alüminyum 5754-H111 Charpy Darbe Tepkisi

Abstract

Bu çalışmada, üç farklı çentik derinliğine sahip alüminyum levhalar, karbon/epoksi ve e-cam/epoksi kompozitleri ile tamir edilmiş ve Charpy darbe tepkileri deneysel olarak araştırılmıştır. Yama melzemeleri [0/45/-45] oryantasyonlu üç eksenli kumaşlar ile takviyelendirimiştir. Bu üç eksenli kumaşlar üst üste konumlanırılarak [90/45/-45/45/-45/90] oryantasyonlu kompozit laminalar oluşturulmuştur. Laminaların oluşturulmasında el yatırması tekniği kullanılmıştır. El yatırması ile ıslatılan takviye kumaşları 100 °C ve 7 bar basınç altında kürleştirilmiştir. Hem alüminyum hemde onarım elemanlarının boyutlandırılmasında su jeti kullanılmıştır. Boyutlandırılmış alüminyum ve onarım elemanları, çift bileşenli metil metakrilat yapıştırıcı ile tek taraflı olarak birbirine yapıştırılmıştır. Deneysel aşamada öncelikle kompozitlerin bazı mekanik özellikleri belirlenmiştir. Sonrasında üç farklı çentik boyundaki (3mm, 5mm, 7mm) onarılmış ve onarılmamış alüminyum levhaların enerji emme miktarları Charpy çentik darbe deneyleri ile tespit edilmiştir. Ayrıca kompozit yamaların Taramalı Elektron Mikroskobu (SEM) analizi yapılmıştır.

Keywords

• Charpy darbe tepkisi
• E-cam
• Karbon fiber
• Epoksi

Charpy Impact Response of Notched Aluminum 5754-H111 of Repaired with Carbon/Epoxy and E-Glass/Epoxy

Abstract

I this study, aluminum sheets with three different notch depths were repaired with carbon/epoxy and e-glass/epoxy composites and than were investigated experimentally for their response to Charpy impact. [90/45/-45] oriented triaxial fabrics were used in patch reinforcement materials. Composite laminates were performed in [90/45/-45/45/-45/90] orientation by placing these three axial fabrics on top each other. Hand lay-up technique was used in the creation of laminated composites. The reinforcement fabrics wetted by hand lay-up were cured by hot molding at 100 °C and 7 bar pressure. Water jet was used for sizing both aluminum and repair elements. The sized aluminum and repair elements were glued to each other as one-side with a double component methyl methacrylate adhesive. In the experimental stage, some mechanical properties of the composites were determined first. Afterwords, of the aluminum plates as repaired and unrepaired in three different notch lengths (3mm, 5mm, 7mm), energy absorption was determined by conducting Charpy notch impact tests. In addition Scanning Electron Microscope (SEM) analysis of composite patches were performed..

Keywords

• Charpy impact response
• E-glass
• Carbon fiber
• Epoxy

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