Fatigue strength of L610-P wing-fuselage attachment lug made of glare 2 fibre-metal laminate

摘要

Flight simulation fatigue test was carried out on a lug specimen representing half of the wing-fuselage attachment lug designed for 60-apssenger aircraft L610-P (product of Let Kunovice,Czech Republic).the specimen was made of GLARE 2 fibre-metal laminate with the maximum thickness 18.25 mm in the hole region.Initiation of fatigue cracks was watched and their growth was measured during the test.Crack growth rate was found decreasing with increasing crack length land 100 times lower with repsect to crack growth rate in an Al-alloy lug.Fatigue life of the lug subjected to a typical-flight loading history was 10 times longer than a designed life of the aircraft.