The aim of the present investigation is to perform both an experimental and a theoretical study of the behavior of cracks in GLARE loaded under a combined mode I and mode II loading, using the angled crack problem. Cracks originating from impact damage in aircraft fuselages can experience a mixed mode I and II load at the start of their life. For GLARE, the more fibrous nature of GLARE compared to aluminium may change the propagation. The experiments were performed on specimens made of GLARE-3, with the main material directions aligned with the specimen axis. As reference materials, both aluminium 2024-T3 and 7075-T6 are used. For angled cracks, the propagation direction has been predicted by Erdogan and Sih, Williams and Ewing and Theocaris et al.
Experimental Study of the Angled Crack in GLARE 3
1994
66 pages
Report
No indication
English
Aircraft , Composite Materials , Nonferrous Metals & Alloys , Engineering Materials , Aircraft construction materials , Aluminum alloys , Crack propagation , Laminates , Fuselages , Aircraft maintenance , Cracking(Fracturing) , Stress analysis , Mathematical models , Failure analysis , Loads(Forces) , Foreign technology , GLARE
Post-Impact Biaxial Fatigue Crack Growth in Glare
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