• Proceedings of the Korean Institute of Industrial Safety Conference
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• 1998.05a
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• pp.57-62
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• 1998

구조물이나 기계요소내의 결함이 성장하여 파손(Failure)에 이르는 현상은 공학분야에서 중요하게 평가되어 오고 있다. 반복적으로 변하는 응력에 의하여 결함이 초기 성장을 거쳐 재료의 파손에 이르게 되는 과정인 피로파괴는 파괴역학의 한 중요한 분야이다. 이에, 본 연구에서는 열처리의 특성상 부식환경에 매우 민감한 Al-Zn-Mg-Cu Alloy 7075에 대하여 Peak Aged T65l Tempering을 실시한 Al-Alloy 7075-T65l에 대하여 각기 환경(대기, 물, 해수)의 변화가 부식피로균열성장에 미치는 영향과 부식환경에서의 긴 균열(Long Crack)과 짧은 균열(Short Clark)의 부식피로균열 성장특성을 비교, 고찰하여 초기균열의 잠재시간과 안정성장 시간을 예측하여 구조물의 수명예측 및 안전성 평가에 기여 할 수 있는데 목적이 있다. (중략)

• Journal of Ocean Engineering and Technology
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• v.27 no.1
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• pp.37-42
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• 2013

The presence of a crack can increase the local stress or strain, which can cause inelastic deformation and significantly reduce the life of a component or structure. Therefore, in this study, the fatigue crack growth (FCG) behaviors of friction stir welded Al 2024-T3 and Al 7075-T6 specimens were examined, with fatigue cracks growing parallel to the dynamically recrystallized zone at variable ${\Delta}K$ values and an R ratio of 0.3. In addition, the FCG values of the base metal Al 2024-T3 and Al 7075-T6 were tested under the same conditions and parameters as comparative groups. The results showed that compared with the base metal Al 2024 specimen, which had the best fatigue property, the welded specimen had only 88% of the fatigue cycles.

• Proceedings of the KSME Conference
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• 2000.11a
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• pp.268-273
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• 2000

Mechanical properties of the materials used for transportations and industrial machinery under high strain rate loading conditions are required to provide appropriate safety assessment to these mechanical structures. The Split Hopkinson Pressure Bar(SHPB) technique, a special experimental apparatus, can be used to obtain the material behavior under high strain rate loading condition. In this paper, dynamic deformation behaviors of the aluminum alloys, Al2024-T4, Al6061-T6 and Al7075-T6, under high strain rate compressive and tensile loading are determined using SHPB technique.

• Journal of Korea Foundry Society
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• v.24 no.6
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• pp.340-346
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• 2004

The plan for obtaining a good combination of strength and castability appeared feasible and the following observations were made. 1. In Al-12Mg-6.6Zn-xSi alloys, more primary $Mg_2Si$ phase formed with reduced $Al_3Mg_2$ phase, as Si content is necessary for an effective solution heat treatment because the solidus temperature is very low silicon contents. 2. A high tensile strength could be obtained in the heat-treated Al-12Mg-5.5Zn-5Si alloy attributed in the heat-treated Al-12Mg-5.5Zn-5Si alloy attributes to fine $MgZn_2$ particles that precipitated uniformly in the matrix. 3. Al-12Mg-5.5Zn-Si alloys showed excellent casting capabilities such as hot cracking resistance and fluidity compared to the reference commercial alloys. 4. The wear resistance of Al-12Mg-5.5Zn-5Si alloy was superior to that of A7075 alloy, and even higher resistance is expected if the morphology and size of primary $Mg_2Si$ phase is carefully controlled.

• Proceedings of the KSME Conference
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• 2007.05a
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• pp.274-278
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• 2007

The purpose of this study is to analyze the important loads related with crack-growth in aircraft. Al Alloys mainly used in aircraft are Al2024 and Al7075 in Duralumin. In random fatigue loading, it has been understood crack-growth characteristic using fractured surface photograph by SEM. In order to obtained CTOD, we measured a crack size in wing frame part. As a result of fatigue experiment that accumulating plenty of fatigue loadings, we find more cracks than that produces in the same fatigue loading. The important loads relating to crack-growth was found in the largest strain cycle. Applying strain block in fatigue experiment, it is actually loading in connection of aircraft. In conclusion, These results can be used for preventing an accident owing fatigue-fracture in aircraft.

• Proceedings of the Korean Powder Metallurgy Institute Conference
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• 2006.09a
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• pp.536-537
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• 2006

In the present work, the sintering behavior of high strength Al-5.6Zn-2.5Mg-1.6Cu (in wt.%) alloy compacts prepared from elemental powders was investigated. Microstructural evaluation was accompanied by XRD and DSC methods in order to determine the temperature and chemical composition of the liquid phases formed during sintering. It was found that three transient liquid phases are formed at 420, 439 and 450 $^{\circ}C$. Microstructural study revealed the progressive formation of sintered contacts due to the presence of the liquid phases, although the green compact expands as a result of the melt penetration along the grain boundaries. While Zn melts at ${\sim}420\;^{\circ}C$, the intermetallic phases formed between Al and Mg were found to be responsible for the formation of liquid phase and the dimensional change at higher temperatures.

• Journal of the Korea Institute of Military Science and Technology
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• v.5 no.4
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• pp.67-77
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• 2002

This paper introduces the calibration results of the fatigue crack growth models for damage tolerance analysis of the aircraft structures. Generalized Willenborg model and Wheeler model are calibrated with experimental data tested under the load spectrum of a trainer. The retardation factors such as, shut-off ratio in Generalized Willenborg model and shaping exponent in Wheeler model, are evaluated for aluminum alloys AL2024-T3511, AL7050-T7451 and AL7075-T73511. It is shown that the retardation effect of the crack growth rate depends on the yield strength of material and the maximum stress in the load spectrum. Generalized Willenborg model and Wheeler model give satisfactory prediction of crack growth life but the calibration of the experimental parameters with test is required.

• Corrosion Science and Technology
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• v.6 no.4
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• pp.206-210
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• 2007

Aerospace aluminum alloys such as Al alloy 2024-T3 and 7075-T6 are subject to localized corrosion due the existence of intermetallics containing Cu, Mg or Zn. Chromate is currently widely used in the aerospace industry as the corrosion inhibitor for these alloys. However, chromate needs to be replaced due to its strong carcinogenicity. In this study, an extensive pigment screening has been performed to find replacements for chromates. Different categories of inhibitors were evaluated by immersion tests, DC polarization tests and other methods. Phosphates, zinc salts, cerium salts, vanadates and benzotriazole were found to be effective inhibitors for AA7075. Among those inhibitors, zinc phosphate was found to be the most effective in our novel, silane-based, one-step aqueous primer system. The performance of this primer is comparable to that of currently used chromate primers in accelerated corrosion tests, while it is completely chromate-free and its VOC is about 80% less than that of current primers. Studies by SEM/EDS showed that the unique structure of the superprimer accounts for the strong anti-corrosion performance of the zinc phosphate pigment. The self-assembled stratified double-layer structure of the superprimer is characterized by a less-penetrable hydrophobic layer at the top and a hydrophilic layer accommodating the inhibitors underneath. The top layer functions as the physical barrier against water ingress, while the lower layer functions as a reservoirfor the inhibitor, which is leached out only if the coating is damaged by a scratch or scribe. The presence of a silane in the primer further improves the adhesion and anti-corrosion performance of the primer.

• Proceedings of the KSME Conference
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• 2007.05a
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• pp.1601-1606
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• 2007

In order for high strength aluminum alloys to be used in transportation systems and the aerospace industry, excellent mechanical and physical properties are required. In particular, excellent anti-abrasion property is indispensable for parts that require driving force. In general, surface treatment technologies such as high frequency heat treatment, gas solid carburizing, surface rolling, shot peening are used as ways of improving anti-abrasion property. Among various surface treatment technologies, this research chose shot peening processing for Al7075-T6, which is well known as representative high-strength alloy steel. Wear characteristics were compared and analyzed after shot peening processing with shot ball velocities of 40m/s and 70m/s in order to investigate the effects of shot peening processing on wear characteristics.

• Journal of Welding and Joining
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• v.5 no.1
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• pp.42-56
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• 1987

Fatigue Fracture behaviors of the TIG-welded aluminum alloys, such as Al 2024-T4, A1 5050-0 and Al 7075-T7 were investigated when a crack propagated from tensile residual stress region and compressive residual stress region. The experimental values were compared with the values expected by the Forman equation. The experimental results are summarized as the following: (1) In case of fatigue crack propagation from residual stress region, the values predicted by Forman equation were Found to exactly corresponded to the experimental values. (2) When the stress intensityfactors affected by compressive residual stress, Kres, were greater than the stress intensity factors by minimum applied stresses. Kmin, the Forman equation was found to be improper to be applied directly, but the equation appeared to be proper, if the stress ratio was modified to zero. (3) The experimental results confirmed that residual stress was relaxed by repeated tensile loading and the relaxing trend was greater in case of compressive residual stress than that of tensile residual stress.