Titanium alloy is widely used in aviation

aerospace

marine and other fields for its high strength

good corrosion resistance and high heat resistance. Lots of aircraft structures were manufactured by titanium alloys

such as the pulley frame

hinge joint and the base structure

which relate to lug connection parts. In order to investigate the failure behavior and optimize the geometric shape

the static-load tests were carried out on the titanium alloy lugs. The effect of lug shape and loading method on the failure behavior has been studied

and K 0 and K con1 have been calculated. Meanwhile

typical fracture mechanisms of the titanium alloy lugs were given in present research.