FATIGUE STRENGTH SIMULATION OF AIRCRAFT LUG
1. mr Slobodanka Boljanović, High School of Mechanical Engineering, Belgrade, Serbia
2. STEVAN MAKSIMOVIĆ, Vojnotehnički Institut Beograd, Serbia
A computational models for the strength estimation of cracked aircraft lug are formulated. The crack growth propagation is investigated through the stress analysis and fatigue life calculation. The stress field around the crack tip and the stress intensity factor are evaluated by applying analytical approach. The fatigue life up to failure is simulated by employing two different crack growth laws. The estimations are compared with avaiable experimental data, and good correlation between different results are obtained.
Ključne reči : : fatigue crack growth aircraft lug strength evaluation
Tematska oblast:
Mechanics and Design
Datum:
13.05.2015.
