ABSTRACT
Fibre-metal laminates (FMLs) are structural composites designed aiming to produce a damage-tolerant and high strength material. Their application in aeronautical structures demands a deep knowledge of a wide set of mechanical properties and technological values, including both fracture toughness and residual strength. The residual strength of fibre-metal laminates (FMLs) has been traditionally determined by using wide sheet (M(T)) specimens. The use of this geometry requires large quantities of material and heavy laboratorial facilities. On the other hand, a methodology for critical fracture toughness evaluation has been proposed recently, which uses small SE(B) and C(T) specimens as suggested by ASTM standards. Fracture toughness (Jc) of Arall 0.3 laminates was measured employing this methodology on C(T) specimens with W= 50.0 mm. Additionally, residual strength values of M(T) specimens with W = 200.0 mm and 2a/W ratios between 1/4 and 1/3 were experimentally obtained. Based on Jc results from C(T) specimens the residual strengths of the M(T) specimens were predicted. These values were compared to the experimental ones. Results showed very good agreement between them.
