Fracture and fatigue of damage tolerant Al-Li sheet alloys

Corrosion fatigue crack arrest in aluminium alloys

The economic life of airframes is largely determined by widespread initiation and growth of fatigue cracks at low stress intensities. Any factor reducing the low stress intensity fatigue damage rate could, if controllable, increase the structural durability. One such factor is corrosion fatigue crack arrest. Corrosion product build-up within a...

Flight simulation fatigue crack propagation in single and double element lugs

Flight simulation fatigue crack propagation tests on single and double element lugs made from 2024-T351 and TOT5-TT351 aluminium alloys and Ti-6AJ.-UV titanium alloy were carried out. Initial damage was a throughthickness notch at one side of each hole in one element. Results showed that crack propagation lives for double element lugs were much...

Fractography of stress corrosion in Ti-8A1 tested in fatigue

A fractographic examination was made of unnotched aged and solution treated Ti-8A1 specimens subjected to fluctuating tension fatigue in air, 3% aqueous NaCl and methanol-HC1. Crack initiation in air and 3% NaCl probably occurred from reversed slip. Crack initiation in methanol-HC1 was by intergranular dissolution. Corrosion along slip bands was...