Investigation of Fatigue Crack Growth in a Landing Gear Support Fitting

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Ghodoosi, Hamed | 2014

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 45823 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Adib Nazari, Saeid
Abstract:
In this thesis failure analysis of a critical part in a landing gear of a commercial aircraft was conducted.Fatigue phenomenon was determined as the reason for the failure and fracture of the mentionedcomponent. Fractography investigation of the fracture surface and charasteristicswas conducted.Scanning Electron Microscope was utilized for the study of the fracture surface. In the fracture surface, fatigue striations were observed. An experimental model of the crack growth is presented by using the fracture surface characteristics. By counting the fatigue striations and measuring their distance betwwn them on the fracture surface, the rate of the crack growth and crack growth life were calculated. Results demonstrated that the crack growth life from the first crack initiation to the final fracture of the component was approximately 4720 cycles. Finally, the fatigue crack growth behavior of this specific aluminium alloy which has been investigated by this model was compared with three other aluminum alloys
Keywords:
Fatigue ; Fractography ; Stress Intensity Factor ; Fatigue Striation

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