A Numerical and Experimental Study of Adhesively Bonded Repairs of Aluminum Fuselage Structures Using Aluminum and Composite Patches
Başlık:
A Numerical and Experimental Study of Adhesively Bonded Repairs of Aluminum Fuselage Structures Using Aluminum and Composite Patches
Yazar:
Chadha, Reewanshu, author. (orcid)0000-0002-9872-8467
ISBN:
9780438129467
Yazar Ek Girişi:
Fiziksel Tanımlama:
1 electronic resource (295 pages)
Genel Not:
Source: Dissertation Abstracts International, Volume: 79-11(E), Section: B.
Advisors: Tein-Min Tan; Jonathan Awerbuch Committee members: John G. Bakuckas; Nicholas P. Cernansky; Bor-Chin Chang; Shi-Chieh Cheng.
Özet:
Multi-site cracks may occur in aircraft fuselage structures along the riveted joints as the result of fatigue loading. Traditional repair method is done by removing the damage area and then mechanically fastening a piece of new skin to the fuselage. Adhesively bonded repairs have been shown to be superior than the traditional fastened repairs in restoring the strength of fuselage structures and increasing the service life of the aircraft. Adhesively bonded repairs are beneficial in two key aspects: i) they alleviate the stress concentrations at the fastener holes; and ii) they are structurally and aerodynamically more efficient. Bonded repair technology has been used for military applications for more than two decades, but has not been implemented in commercial aircraft because of the lack of: i) confidence in the ability of adhesive bonded repairs to reduce fatigue crack growth; ii) reliable inspection methods to determine bond quality to ensure strength and durability; iii) appropriate tools for the analysis and design of adhesively bonded repair for curved panels when subjected to realistic flight loading conditions.
In this dissertation, a numerical and experimental study on the durability and integrity of bonded repairs was conducted. Experimental work was performed at the FAA WJH Technical Center using its Full-Scale Structural Test Evaluation and Research (FASTER) facility on two fuselage panels removed from a retired B727. Test results revealed that properly designed and installed bonded repairs are effective in reducing the crack growth rate while the degradation of repair quality, such as reducing the number of plies, reducing patch stiffness, and the presence of disbonds between the patch and panel, affects their effectiveness in containing crack growth. In addition, a finite element based predictive model was developed to simulate the fatigue crack growth in the aluminum fuselage panel repaired with aluminum and Boron/Epoxy patches. The model uses the global-local finite element approach and is capable of simulating fatigue crack growth in a full-scale curved fuselage panel subjected to realistic flight loading conditions as well as the thermal residual stresses developed during the bonding process. The validated model was used to conduct studies on the effect of several key parameters of the laminate configuration of the patch on the fatigue crack growth behavior.
Notlar:
School code: 0065
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Yer Numarası | Demirbaş Numarası | Shelf Location | Lokasyon / Statüsü / İade Tarihi |
---|---|---|---|
XX(695396.1) | 695396-1001 | Proquest E-Tez Koleksiyonu | Arıyor... |
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