• Proceedings of the Korean Society of Precision Engineering Conference
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• 1996.11a
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• pp.1093-1097
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• 1996

The Substitution development of 7075-T6 Al alloy to 7050-T74 Al alloy in small arms to improve anti-stress corrosion cracking was processed along with mass productivity consideration. To meet 7050 Al alloy material characteristics Indirect extrusion type was adopted and local heating above recrystalization temperature in forging process had to be avoided. The T74 aging treatment was 12$0^{\circ}C$ -6hrs and 175$^{\circ}C$ -12hrs and was appropriate for both machanical and anti-cohesion properties. In accessment of field application test 7050Al alloy made parts of small arms showed equivalent or better performance than 7075 Al alloy.

• Proceedings of the Materials Research Society of Korea Conference
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• 1999.11a
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• pp.36-36
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• 1999

• Proceedings of the Materials Research Society of Korea Conference
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• 1995.11a
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• pp.105-105
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• 1995

• Proceedings of the Materials Research Society of Korea Conference
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• 1995.11a
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• pp.121-121
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• 1995

• Korean Journal of Materials Research
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• v.9 no.7
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• pp.695-700
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• 1999

Effects of two-step aging treatment on the stress corrosion cracking(SCC) resistance of 7050 Al alloy were investigated by transmission electron microscopy, electrical conductivity measurement and stress corrosion facter(SCF) evaluation. It was found that η', principal hardening phase, transformed to η during over aging above maximum hardness, and SCC resistance was improved by increasing of the size and interspacing of η particles in matrix and grain boundary. The electrical conductivity increased with aging time, but SCF decreased due to the decrease of yield strength. This results mean increase of SCC resistance The optimum two-step aging condition in forged 7050 Al alloy was to be first aged at $120^{\circ}C$ for 6h and then finally aged at $175^{\circ}C$ for 12h.

• Analytical Science and Technology
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• v.7 no.4
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• pp.527-540
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• 1994

The surface microstructure modification by $N^+ion$ implantation into 7050A1 alloy was investigated. Ion implantation method is to implant physically accelerated ions to the surface of a substrate. High doses of nitrogen($5{\times}10^{15}ions/cm^2$, $5{\times}10^{17}ions/cm^2$, $8{\times}10^{17}ions/cm^2$) were implanted into 7050A1 alloy using accelerating voltage of 100KeV and current density of $23.1{\mu}A/cm^2$. The implanted layers were characterized by EPMA, AES, XRD, and TEM. The experimental results were compared with computer simulation data. The results showed that AlN was formed from the surface to $4000{\AA}$ depth with Gaussian distribution and the damage region was also observed. This surface modification by $N^+ion$ implantation increased the microhardness of 7050A1 alloy surface.

• Proceedings of the Korean Society for Technology of Plasticity Conference
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• 2001.10a
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• pp.228-232
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• 2001

Fatigue strength, electrical conductivity and stress-corrosion-cracking resistance are considered as important factors at aircraft Al alloys, therefore Al7050 alloy has been developed to improve such properties. However, hammer-forged Al7050 parts showed the undesirable structures such as severe local grain coarsening and inhomogeneous material flow, resulted in the degraded mechanical properties. In this paper, process conditions are investigated for elimination of the grain coarsening and improved material flow during forging process by both of experiments and FEM analysis. Particular interest has been given to understand role of preform shape on the grain coarsening behavior and magnitude of the hammer forging load The use of preform has been beneficial for reduction of the forging load and elimination of the grain coarsening. However, in the cases of as received bar and the round bar, which was machined to 2.5mm thickness in surface layer, some degree of local grain coarsening behavior has been observed. The optimized preform shape could be properly designed by applying the FEM simulation.

• Journal of the Korean Society for Heat Treatment
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• v.9 no.2
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• pp.139-146
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• 1996

The aero-industry is union industry which includes a research development type, a knowledge accumulation type and a developed country type. The aero-industry of Korea is in semi-developed type stage but departed later than that of other country such as Taiwan, Indonesia etc. Therefore, the necessity of domestic airplane material is required. This study on 7050Al extruded alloy aims to suggest an adequate heat treatment conditions of T73, T74 and T76. The results of this study show that; 1. The optimum conditions of T7x heat treatment in extruded 7050Al alloy show this; $$T73:121^{\circ}C{\times}7hr+177^{\circ}C{\times}14hr$$. $$T74:121^{\circ}C{\times}7hr+177^{\circ}C{\times}10hr$$. $$T76:121^{\circ}C{\times}7hr+163^{\circ}C{\times}21hr$$. 2. The 2nd step aging heat treatment such as T73, T74 and T76 etc. is efective in 7050Al alloy but the variation otf microstructure and mechanical property with dispersive inclusions produced for extrusion process causes some troubles. Accordingly, in order to produce a good 7050Al alloy, a careful attention is needed in manufacturing process.

• Korean Journal of Materials Research
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• v.7 no.9
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• pp.789-794
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• 1997

7050AI합금의 미세조직 및 기계적성질에 미치는 2단시효처리의 영향을 투과전자현미경, 열분석, 경도시험 및 인장 시험을 통하여 조사하였다. 12$0^{\circ}C$에서 6시간 1차 시효처리한 후 1$65^{\circ}C$와 175$^{\circ}C$에서 2차 시효처리하였을때 1$65^{\circ}C$에서는 6시간 시효시 최대경도값 201.3Hv를 나타내었고, 175$^{\circ}C$에서는 3시간 시효처리하였을때 최대경도값 197Hv를 나타내었다.

• Journal of the Korean Society for Heat Treatment
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• v.12 no.2
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• pp.129-135
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• 1999

The effects of Ag addition on the microstructures and mechanical properties of 7050 Al alloy were investigated. Various homogenizing and aging treatments were carried out to analyze the controversial effects of Ag in 7050 Al alloy. Transmission electron microscopy(TEM) was used for microstructural analysis. The hardening precipitates(${\eta}^{\prime}$) become finer with Ag addition. It suggests that Ag promotes easier nucleation of ${\eta}{\prime}$. The strength of overaged Ag bearing alloys are higher than that of Ag free alloy. Hardening precipitates(${\eta}^{\prime}$) in Ag bearing alloys are smaller than that of Ag free alloys, because the growth rate of ${\eta}^{\prime}$ during overaging stage is lower in Ag bearing alloys.