Author(s):
1. Slobodanka Boljanović, High School of Mechanical Engineering, Belgrade, Serbia
2. Stevan Maksimović, Vojnotehnički Institut Beograd, Serbia

Abstract:
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.

Key words:
: fatigue, crack growth, aircraft lug, strength evaluation

Thematic field:
Mechanics and Design

Date of abstract submission:
13.05.2015.

Conference:
12th International conference on accomplishments in Electrical and Mechanical Engineering and Information Technology (DEMI 2015)

Final paper Abstract