• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 춘계학술대회논문집A
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• pp.424-429
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• 2001

Residual stresses can be produced during manufacturing processes, eg. welding, machining and plastic working, and also in service. It can be superimposed with externally applied loads, so that unexpected deformations and failures of members will be occurred. Especially, the strength and the life of welded components are affected extensively by the residual stresses distributed around their weldments not only under static loads, but also fatigue loads. These residual stresses are not kept constant, but relaxed or redistributed during service. Under static loads the relaxation takes place when the residual stress superimposed with external stress exceeds locally the yield stress of material used. It is shown that under fatigue loads the residual stress is considerably relieved by the first or few cycle loading, and then gradually relaxed with increasing loading cycles. Although many investigations in this field have been carried out, the phenomenon and mechanism of the stress relaxation by mechanical means are still not clear, and there are few comprehensive models for predicting specific effects on the stress relaxation. In this study, the effects of applied static and fatigue loads on the residual stress relaxation were Investigated, and a model to predict quantitatively the residual stress relaxation was proposed.

• 한국항공운항학회지
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• 제10권1호
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• pp.57-68
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• 2002

The economical aspects should be evaluated to decide the LCC(Life Cycle Cost) of the long life facilities or equipments. Airplane operators evaluate the economical aspects to decide whether they maintain the existing airplane or substitute the new one. This paper presents economic life cycle and economic life cost for both Cessna 172R and Mooney 20J that are operated for flight training in 'H' University. The residual value that is used to calculate the capital recovery rate of the airplane is calculated based on the data from Blue Book published in USA. The annual equivalent on operation cost is calculated based on the 500 flight hours per year which is the annual flight hour for the airplane in 'H' university. This paper showed that economic life cycle of Cessna 172R is nine years since it was introduced in 2001, and Mooney 20J which was introduced in 1991 exceeds the economic life cycle in 2002.

• 한국전산구조공학회:학술대회논문집
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• 한국전산구조공학회 1991년도 가을 학술발표회 논문집
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• pp.29-32
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• 1991

It is well known that the fatigue damage process in composite materials is very complicated due to complex failure mechanisms that comprise debounding, matrix cracking, delamination and fiber splitting of laminates. Therefore, the residual strength, instead of a single dominant crack length, is chosen to describe the criticality of the damage accumulated in the sublaminate. In this study, two models for residual strength degradation established by Yang-Liu and Tanimoto-Ishikawa that are capable of predicting the statistical distribution of both fatigue life and residual strength have been investigated and compared. Statistical methodologies for fatigue life prediction of composite materials have frequently been adopted. However, these are usually based on a simplified probabilistic approach considering only the variation of fatigue test data. The main object of this work is to propose a fatigue reliability analysis model which accounts for the effect of all sources of variation such as fabrication and workmanship, error in the fatigue model, load itself, etc. The proposed model is examined using the previous experimental data of GFRP and it is shown that it can be practically applied for fatigue problems in composite materials.

• Journal of Welding and Joining
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• 제20권2호
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• pp.59-64
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• 2002

When the vehicle travels in an actual road, resistance spot weldments of the vehicle structure are exposed to complex loading state. Since the fatigue strength in resistance spot weldment of vehicle body can be determined by effect of residual stresses and loading state of driving, estimating actual loading state and considering residual stress effect are needed. In this study, Fatigue stress-fatigue life relation concerned residual stress effect was obtained by thermo elastic plastic finite element analysis. And applied loading in resistance spot weldments of vehicle body was calculated by dynamic analysis. Presumption of fatigue life was performed using proposed method

• 대한기계학회논문집A
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• 제27권6호
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• pp.987-996
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• 2003

The structural integrity of the reactor vessel with the approaching end of life must be assured for pressurized thermal shock. The regulation specifies the screening criteria for this and requires that specific analysis be performed for the reactor vessel which is anticipated to exceed the screening criteria at the end of plant life. In case the screening criteria is exceeded by the deterministic analysis, probabilistic analysis must be performed to show that failure probability Is within the limit. In this study, probabilistic fracture mechanics analysis of the reactor vessel for pressurized thermal shock is performed and the effects of residual stress and master curve on the failure probability are investigated.

• 한국안전학회지
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• 제16권2호
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• pp.27-35
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• 2001

For the purpose of healing the degradation part, $CO_2$ laser beam was irradiated with different irradiation condition (porer, diameter, velocity and beam type) to find out optimum irradiation condition. The test series of hardness, residual stress measurement, and fatigue were carried out after the irradiation. Experimental results show that micro-hardness values on the surface of the irradiated specimens m approximately 2.5 times higher than those of un-irradiated ones. Fatigue tests show that the fatigue life was improved by the compressive residual stress after laser beam irradiation. However, some specimens with different conditions show the shorter fatigue life. It means that laser beam irradiation with optimum irradiation condition and optimum absorb energy, Q can improve the fatigue strength.

• 한국정밀공학회지
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• 제20권3호
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• pp.165-171
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• 2003

In a structure, many components are fastened together using bolts, nuts and rivets through drilled holes. Not only do these fastened joints enable easy assembly and dismantling, they are also able to transfer as well as to distribute loads applied onto the structures. The major drawback of such connections, however, is that the fatigue life of the components is reduced by the presence of the hole since the stress concentration around the hole is increased. In addition, the hole drilling process itself may introduce defects or roughness at the surfaces of the hole that may cause further decrease in fatigue performance of the components. For applications where fatigue loadings are important, one way to compensate the decrease in fatigue life of the components is by introduction of beneficial compressive residual stress around the hole using cold working. The material used for this research were A12024-T351 and A17050-T7451 using the primary member of aircraft. We present, In this paper, the characteristics of coldworking by evaluation of the hole expansion ratio, residual stress distribution, and fatigue properties.

• 한국해양공학회지
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• 제17권2호
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• pp.47-53
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• 2003

The development of new materials with light weight and high strength has become vital to the machinery, aircraft and auto industries. However, there are a lot of problems with developing such materials that require such expensive tools, as well as a great deal of time and effort. Therefore, the improvement of fatigue life through, the adoption of residual stress, is the main focus. The compressive residual stress was imposed on the surface according to each shot velocity(1800, 2200, 2600, 3000rpm) based on Shot-peening, which is the method of improving fatigue life and strength. By using the methose mentioned above, we arrived at the following conclusions; 1. The fatigue crack growth rate(da/dN) of the Shot-peened material was lower than that of the Un-peened material. In stage I, $\Delta$K$_{th}$, the threshold stress intensity factor, of the shot-peen processed material is high in critical parts, unlike the Un-peened material. Also m, fatigue crack growth exponent and number of cycle of the Shot-peened material was higher than of the Un-peened material. That is concluded from effect of da/dN. 2. Fatigue life shows more improvement in the Shot-peened material than in the Un-peened material. Compressive residual stress of the surface on the Shot-peen processed operate resistance force of fatigue crack propagation.

• 한국군사과학기술학회지
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• 제2권1호
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• pp.101-109
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• 1999

본 논문은 항공기 구조물의 체결용 홀(hole)을 냉간가공(cold working)할때 홀주변에 생성되는 잔류응력이 균열발생 수명과 균열성장에 미치는 영향을 연구한 내용이다. 항공기용 재료로 많이 사용되는 AL7075-T6 및 AL2024-T3 시편으로 측정된 계수를 Morrow의 수명예측식에 적용하여 수정된 냉간가공(cold working)에 관한 수명예측식을 제안하였다. 수정된 계산식으로 얻어진 수명예측값과 실험에 의하여 이미 알려진 값이 비교적 일치함을 보여 이러한 재료에 대하여 수명예측이 가능함을 보였다. 균열성장 예측을 위해 역시 AL7075-T6 재료에 대하여 가중함수(weight function)방법으로 잔류응력 세기계수를 구하여 Forman의 균열성장 예측식을 수정하여 계산 한 결과 이 또한 알려진 실험값과 거의 일치함을 보여 실험에 사용한 재료의 구조물 해석에 유용 할 것으로 보인다. 본 연구는 항공기용 구조물의 홀주변을 냉간가공 (cold working)할 때 생성되는 잔류응력의 영향을 연구하는 기초적인 단계 일 뿐이며, 향후 실제 정비현장에서 적용 할 수 있는 대상분야와 연구 방향에 대한 보다 심층적 연구가 필요함을 보인다.

• 비파괴검사학회지
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• 제28권2호
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• pp.125-130
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• 2008

레이저 용접부의 국소 잔류응력을 측정하기 위한 비파괴 기법으로 구형압입시험이 제안되었다. 용접상태 절단휠의 구형압입시험으로 얻어진 겉보기 항복강도와 절단횔 용접부에 대한 응력완화 열처리 이후 동등한 위치에서 구한 고유 항복강도를 정량적으로 비교하였다. 고유항복강도가 탄성한도 내의 잔류응력에 의해서 변화하지 않는다고 고려하면 용융선으로부터 거리에 따른 두 항복강도의 차이가 용접잔류응력의 분포로 나타난다. 레이저 용접된 다이아몬드 절단휠의 구형압입시험으로부터 약 10 mm 폭에 걸친 잔류응력의 분포를 확인하였으며, 잔류응력은 쌩크와 절단팁 내에서 각각 최대 압축 및 인장 잔류응력치를 나타내었다.