• Transactions of the Korean Society of Mechanical Engineers A
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• v.35 no.7
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• pp.717-722
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• 2011

The purpose of this study is to predict the residual stress in Al6061 during T6 heat treatment. In this study, the variable residual stress in case of the solid solution($530^{\circ}C$, 2h) and artificial ageing($175^{\circ}C$, 9h) of Al6061 subjected to T6 heat treatment is determined at different ageing times. A heat treatment experiment is conducted to determine the heat transfer coefficient, on the basis of which the residual stress during the T6 heat treatment is predicted. In order to take into account the relaxation of residual stress during artificial ageing, a Zener-Wert-Avrami function is used and elasto-plastic nonlinear analysis is conducted through FE-simulation. Further, the residual stress is measured by using the X-ray diffraction(XRD) method, and the result is compared with the result from the FE-simulation. It is found that the residual stress predicted form the FE-simulation is in good agreement with the residual stress measured by using the XRD method.

• Journal of the Korea Institute of Military Science and Technology
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• v.2 no.1
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• pp.101-109
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• 1999

The objective of this research is to study effects of the residual stresses on the crack growth and the life of the structure, caused by cold working around the hole of the aircraft structure which will be jointed by rivets and bolts, etc. The compensated Morrow's equation, by experimental data from the materials AL7075-T6 and AL2024-T3, is suggested to calculate the values of the fatigue life prediction of the structure. Also, the compensated Forman's equation, by experimental data from a material AL7075-T6, is suggested to calculate the values of the crack growth prediction of the structure. It is founded that the calculated values from the suggested equations are almost close to the known values of the fatigue life prediction and the crack growth prediction. It is shown that this paper, associated with an initial research on the effects of residual stresses around hole, gives a direction to study the problem at the aircraft maintenance field.

• Proceedings of the KIEE Conference
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• 2008.07a
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• pp.612-613
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• 2008

맥스웰 응력텐서T와 맥스웰 응력 n.T는 물리적인 의미가 없는 가상적인 양이라는 것을 논문 I에서 논하였다. 본 논문 II 에서는 물리적 실체를 가지는 맥스웰 응력텐서의 발산양인 ${\nabla}{\cdot}T$의 계산을 위하여 가상공극을 도입하고, 그 것의 계산법에 대하여 제시한다. 가상공극법은 기존의 여러 전자기력 계산법의 상위개념으로 적용할 수 있는 접근법으로서 매체간에 접촉시에 전자기력 계산을 위하여 개발이 된 것이다. 이 방법을 각 유한요소에 적용함으로서 체적력밀도를 구할 수 있음을 보인다.

• The korean journal of orthodontics
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• v.29 no.5 s.76
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• pp.521-534
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• 1999

The purpose of this study was to find the difference of stress distribution on canine altered by the application point of preangulated T-loop spring. For this study, the finite element models of upper left canine, upper left second premolar and upper left first molar were made. Also, the finite element models of $0.017{\times}0.025$ inch preangulated, preactivated T-loop spring and $0.018{\times}0.025$ inch stainless steel wire were made. Three types of T-loop spring were made . the middle of activated T-loop is positioned in accordance with the middle position of distance of bracket position of both the canine and first molar, 2mm anterior, 2mm posterior. We compared the forces and the distribution of stress that were generated by the difference of position of T-loop spring. The results were as follows. 1. All of the 3 types of T-loop spring showed the similar retraction forces. 2. All showed the similar amount & pattern of stress distribution. 3. The centers of rotation of canine in 3 types of T-loop spring were same and were positioned between C and D plane. 4. The canine showed the intrusive force by 2mm anterior positioned T-loop spring, but the extrusive force by 2mm posterior positioned T-loop suing. Neverthless, because of the small amount of the forces, the effect of vertical force was not significant.

• Magazine of the Korea Concrete Institute
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• v.7 no.3
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• pp.137-148
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• 1995

In this study, a program for evaluation of heat transfer and thermal stress of mass concrete is developed and verified by 2-experiments (internally and externally restricted). Furthermore, the result of the program is compared with those of ADINA-T and ADINA. As a result of the comparison, the proposed method produces comparable results with those from the popular programs (ADIIVA-T and ADINA) and shows the usefulness of the developed program for the evaluation of thermal stresses of mass concrete in both internally and externally restricted structures.

• Proceedings of the Korean Vacuum Society Conference
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• 2011.02a
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• pp.43-43
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• 2011

BN(Boron Nitride)은 온도와 압력 조건에 따라 안정한 상이 sp3 결합인 cubic 구조의 BN(cBN)과 sp2 결합인 hexagonal 구조의 BN(hBN or tBN)으로 나뉘는데, 이 중 cBN은 우수한 기계적, 물리적, 화학적 특성으로 인해 박막 분야에서 매우 높은 응용가능성을 지니고 있다. 하지만 cBN 박막의 합성과정에서의 필수적인 요소인 높은 압축잔류응력은 cBN을 응용분야에 적용하는데 있어 한계점으로 계속 남아 있었다. 그동안 이러한 잔류응력을 감소시키기 위해 열처리, 이온 주입, 제 3의 물질 첨가 등 다양한 관점에서 접근한 연구들이 진행되어 왔다. 본 연구에서는 cBN 합성과정에서 잔류응력을 감소시키기 위한 방법으로 수소를 첨가하였고, 그에 따른 잔류응력의 변화를 분석하고, 그 과정에서 잔류응력의 형성에 수소가 어떤 역할을 하는지 규명하고자 하였다. cBN 박막은 hBN을 target으로한 unbalanced magnetron sputtering를 사용하여, 실리콘 wafer 위에 합성하였다. 증착압력은 1.3mTorr로, 수소의 첨가량을 증가시키며 잔류응력과 cBN fraction을 관찰하였다. cBN fraction은 FTIR로 분석하였고, 잔류응력은 실리콘 strip의 in-situ 곡률측정법으로 계산하였다. cBN 박막의 조성과 구조 분석, 수소의 역할 규명을 위해 RBS 및 HRTEM을 이용하였다.

• Journal of Korean Society of Steel Construction
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• v.14 no.1
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• pp.69-78
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• 2002

This paper describes the analysis results for tensile behavior of tubular column to H-beam connection with T stiffeners. Using the elasto-plastic finite element method, analysis results are compare with experimental results. Parametric analyses with different size of T-stiffener have conducted to understand the stress distribution at the connections. Stress concentration in elastic region and PEEQ distribution in plastic region are plotted for different shape. The results of analysis were applied to design equations and were checked for the applicability of design equations.

• Journal of the Society of Naval Architects of Korea
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• v.28 no.1
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• pp.108-116
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• 1991

In the non-linear behavior of many materials, there is difference between the monotonic behavior by static load and the cyclic behavior by cyclic load. In particular, the short fatigue cracks to propagate in elasto-plastic stress concentrations(notches), are governed significantly by the cyclic behavior of materials. Accordingly, it is needed to investigate and compare the monotonic and cyclic behavior of materials. In the pressent study, the stress-strain relations of materials by monotonic and cyclic load tests were examined for 2 kinds of steels(SS41, HT80) and 5 kinds of Al-alloys(A5083-O, A6N01-T5, A7N01-T4, A7016-T6, A7178-T6). And the constants for mechanical properties of the materials were determined by experimental results, Moreover, when a notch was subjected to cyclic load, the effect of cyclic hardening property of materials on the variation of stress-strain amplitude in the notch tip was discussed by the application of Neuber's rule and experiments for a center notched plate.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.37 no.3
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• pp.387-395
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• 2013

Recently, several circumferential cracks were found in the control rod drive mechanism (CRDM) nozzles of U.S. nuclear power plants. According to the accident analyses, coolant leaks were caused by primary water stress corrosion cracking (PWSCC). The tensile residual stresses caused by welding, corrosion sensitive materials, and boric acid solution cause PWSCC. Therefore, an exact estimation of the residual stress is important for reliable operation. In this study, finite element simulations were conducted to investigate the effects of the tube geometry (thickness and radius) on the residual stresses in a J-groove weld for different CRDM tube locations. Two different tube locations were considered (center-hole and steepest side hill tube), and the tube radius and thickness variables ($r_o/t$=2, 3, 4) included two different reference values ($r_o$=51.6, t=16.9mm).

• Journal of the Korea Institute of Military Science and Technology
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• v.1 no.1
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• pp.154-165
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• 1998

In this paper, the mongrel singular element with 6 node triangle and 8 node quadrilateral element with J-integral are developed and applied to the various plane crack problems for the isotropic material. The convergence nature is excellent for various crack size with even coarse mesh using the direct method. But the results of the mongrel element with J-integral are worse than the former's ones. Fracture tests were conducted on precracked CT specimens. Results show that, for 7075-T6 aluminum wing spar materials, the fracture toughness is 31.06 ksi.inch $\frac{1}{2}$ in the L-T direction.