Abstract
Large deviations have been observed while analysing composite double cantilever beam (DCB) specimens assuming each cracked half as a simple cantilever beam. This paper examines the effect of rotational spring stiffness(K)on the critical fracture energy(GIC)considering nonzero slope at the crack-tip of the DCB specimen by modelling each cracked half as the spring-hinged cantilever beam. The critical load estimates of DCB specimens fromGICare found to be in good agreement with in-house and existing test results of different composite material systems.
Highlights
The lightweight carbon fiber-reinforced composite is found to be more economical for commercial aircraft [1]
Fracture toughness tests have been performed on the double cantilever beam (DCB) specimens made of carbon/epoxy and carbon/PEEK composites
This paper presents a simple and reliable relation for direct evaluation of delamination fracture toughness from the with the crack length of unidirectional DCB specimens made of glass/epoxy composites (B = 25 mm, 2h = 3 mm, E = 36 GPa, K = 8 Nm, and GIC = 286 J/m2)
Summary
The lightweight carbon fiber-reinforced composite (having high stiffness, strength, fatigue and impact resistance, thermal conductivity, and corrosion resistance) is found to be more economical for commercial aircraft [1]. It has become the primary material in many aircraft components (namely, fuselage, wings, and empennage components) [2]. The interlaminar fracture toughness (or the critical strain energy release rate at the onset of crack or damage propagation) is an important fracture property to be evaluated utilizing the fracture mechanics principles. Motivated by the work of the above researchers, this paper examines the effect of rotational spring stiffness on the critical strain energy release rate (GIC) useful for accurate failure load evaluation of delaminated composites. The critical load estimates of DCB specimens from GIC are found to be in good agreement with in-house and existing test data of different composites
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