Akademik Veri Yönetim Sistemi
ARF 2019 – 8. Asian-Australian Rotorcraft Forum, Ankara, Türkiye, 30 Ekim - 02 Kasım 2019
Delamination is one of the main failure mechanisms in composite structures and initiation and propagation of the delamination are controlled by interface parameters including the interlaminar strength and fracture toughness, respectively. Hence, it is crucial to use the correct values of these parameters in design and analysis of components such as composite tapered and curved beams. In this paper, the effect of ply orientation and crack length propagation on Mode I fracture toughness for CFRP and GFRP laminates are investigated. For this purpose, double cantilever beam (DCB) experiments are conducted on CFRP, and GFRP laminates with 0˚//0˚, 25˚//-25˚, 45˚//-45˚, 65˚//-65˚, 25˚//25˚, 45˚//45˚, and 65˚//65˚ interfaces. The delamination propagates from 50 mm to 110 mm for each specimen. Fiber bridging, layer jump, lay-up orientation and material difference effects are clearly seen in these experiments.