Author(s):
1. Stevan Maksimović, Vojnotehnički Institut Beograd, Serbia

Abstract:
Attention in this work is focused on developing computation methods of damaged aircraft structural components with respect fatigue and fracture mechanics. Computation method is based on combining singular finite elements to determine stress intensity factors for cracked structural components with corresponding crack growth lows that include effect of load spectra on number of cycles or blocks up to failure. To demonstrate efficient computation procedure in fatigue life estimation here numerical examples are included. Attention in this work is focused on design of aircraft wing-fuselage joints. Computation procedure to strength analyze with respects fatigue and fracture mechanic is applied to cracked aircraft lug type structure. Computation results are compared with correspond experiments. Good agreement between computation and experimental results is obtained.

Key words:
Fatigue, Fracture mechanics, Aircraft structures, Damaged lugs, Finite Elements, Residual life estimation, Crack growth, Strain energy density method

Thematic field:
MECHANICS AND DESIGN

Opening paper:
Yes

Date of abstract submission:
26.04.2011.

Number of visits:
759

Conference:
11^th International Conference on Accomplishments in Mechanical and Industrial Engineering

Applied paper from author