• 한국자동차공학회논문집
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• 제18권6호
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• pp.38-45
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• 2010

Welding structures are designed to endure its expected life. The most important factors are life. Especially on welded structure, fatigue strength is critical. So this study performed a research on Box and T shape weldment specimen to examine the influence of welding type. In this experiment, the results indicate Box shape was available in more than T shape. Fatigue tests were performed to evaluate the fatigue strength of the both as-welded and statically pre-loaded specimens by 3 point bending load. Fatigue life can be improved by using Ultrasonic Impact Treatment(UIT) effect. Ultrasonic Impact Treatment(UIT) is excellent for eliminating the tensile residual stresses and generating compressive residual stresses which elevate fatigue strength of welded structures. Also, this shows that welding part has better fatigue life and welding was performed well. In this study, to evaluate the Ultrasonic Impact Treatment(UIT) effect, for welding structure, the experiment was conducted at various levels of stress range between 100MPa and 500MPa. From the test results, it was indicated that fatigue performance was improving by Ultrasonic Impact Treatment(UIT)

• 패션비즈니스
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• 제17권2호
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• pp.179-196
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• 2013

This research is about the mechanical properties of knit pullover of Shaping and WholeGarment according to structured patterns and form of the armhole. For the study 12 samples are prepared under different conditions and through comparative analysis of each sample's armhole around armpit in basic properties, tensile strength & elongation and residual elongation after repeated extensions, the conclusion is as follows. As a result of comparing basic properties of structured pattern of Shaping and WholeGarment samples, in all structured patterns Shaping samples weighed more. According to the comparative analysis of tensile strength & elongation of Shaping and WholeGarment samples, Machi on both sides of WholeGarment samples showed the highest strength. By comparing outcome of residual elongation by structured pattern of Shaping and WholeGarment samples, both types were observed to have the residual elongation increase in the order of Plain

• 콘크리트학회논문집
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• 제28권1호
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• pp.95-104
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• 2016

강섬유가 보강된 콘크리트의 지반 바닥슬래브는 소성해석법인 항복선 이론을 바탕으로 평균강도 개념인 등가 휨 강도비로서 설계 휨강도를 평가하였다. 최근 유럽의 설계기준에서는 강섬유에 의한 인장성능을 균열이후의 잔류 휨강도를 직접 평가하도록 하였다. 따라서, 본 연구에서는 기존의 등가 휨강도비와 잔류 휨강도에 따른 인장성능을 실험적으로 평가하고, 하중의 등가 접촉반경과 상대강성반경 비에 의해 하중 위치별 휨 내력을 평가하였다. 설계 휨 내력은 ACI 360R-10 기준이 TR 34 (2003 & 2013)에 비해 과소 평가하였다. 또한, 잔류 휨강도로서 평가하는 TR 34 (2013)은 등가 휨강도비로 계산되어진 TR 34 (2003)의 휨 내력에 비해 다소 작게 평가하고 있지만, 그 차이는 크지 않았다.

• 한국안전학회지
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• 제18권1호
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• pp.1-7
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• 2003

The objective of this paper was to investigate the welding characteristics according to the restraint condition. the pass number, and the shield gas quantity with titanium commonly using in power stations, aircrafts, ships, and so forth. The residual stress distribution was measured under restraint and nonrestraint welding conditions. The tensile strength and elongation of the 4 pass welded specimen were shown higher about 10% and 30% than those of the 7 pass welded specimen at the same welding conditions respectably. Also, the more shield gas quantity and the shorter natural cooling time, the higher tensile strength and the lower elongation.

• 한국정밀공학회지
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• 제29권6호
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• pp.654-663
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• 2012

Damage induced by low velocity impact loading in aircraft composite is the form of failure which is frequently occurred in aircraft. As the consequences of impact loading in composite laminates, matrix cracking, delamination and eventually fiber breakage for higher impact energies can be occurred. Even when no visible impact damage is observed, damage can exist inside of composite laminates and carrying load of the composite laminates is considerably reduced. The objective of this study is to evaluate and predict residual strength behavior of composite laminates by impact loading and for this, tensile test after impact was carried out on composite laminates made of woven CFRP.

• 한국강구조학회 논문집
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• 제16권5호통권72호
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• pp.519-528
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• 2004

대부분의 용접재는 용접 후 빠른 속도로 냉각하는 과정에서 재료조직의 변화, 즉 상변태(마르텐사이트변태)가 일어난다. 그리고 이러한 상변태에 의한 체적의 팽창은 특히 고강도강재의 용접시 용접부의 잔류응력완화에 기여한다. 따라서 고강도강을 적용한 강구조물 접합부의 잔류응력 특징을 파악하기 위해서는 고강도강 용접시 상변태가 잔류응력완화에 미치는 효과를 정량적으로 평가할 수 있는 수치적 모델을 확립해야 한다. 본 연구에서는 고강도강 용접시 상변태에 의한 체적의 팽창이 잔류응력 완화에 미치는 영향을 잔류응력 측정 실험을 통하여 조사하였고, 이를 바탕으로 상변태에 의한 잔류응력완화를 고려한 고강도강 및 이종강재 용접접합부의 잔류응력 특징을 3차원 열탄소성 해석기법 개발을 통하여 재현하였다.

• 한국항공운항학회지
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• 제20권1호
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• pp.103-111
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• 2012

This study reviews several fracture models for predicting the residual strength of notched composite laminates. Representative experimental results on the residual strength of composite laminates containing a notch subjected to static uniaxial tensile loading have been collected from open literature. And notched strength data for T300/5208 are analyzed. The various parameters associated with the fracture models have been determined for laminates. Notched strength data sets are compared with fracture models and the applicability of the different fracture models in predicting the notched strength of composite laminates is discussed. And static tests have been performed on 2.0mm depth notched specimen. And the test results are compared with analysis models.

• 대한조선학회논문집
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• 제38권4호
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• pp.75-82
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• 2001

건조 후 수행하는 수압시험 또는 화물의 적재 등과 같은 정하중은 파랑변동하중에 비하여 선체구조물에 상당히 큰 응력을 유발한다. 이러한 정하중이력에 의하여, 선체구조물의 응력집중으로 인해 피로강도가 문제되는 용접이음부에서는, 재료의 탄소성 거동에 의하여 초기용접잔류응력이 상당히 이완될 것으로 예상된다. 따라서, 이러한 용접이음부의 피로강도를 평가할 때에는 이완된 잔류응력의 영향을 고려하는 것이 보다 합리적이다. 본 연구에서는 선체구조물의 여러 가지 용접형태 중 Padding plate가 용접된 형태에 대하여 정하중이력($0.5{\sigma}Y,\;0.85{\sigma}Y$)에 의한 초기 용접잔류응력의 변화를 측정하며, 잔류응력의 변화가 피로강도에 미치는 영향을 검토한다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집A
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• pp.186-191
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• 2001

Tensile residual stress happen by difference of coefficients of thermal expansion between fiber and matrix is one of the serious problems in metal matrix composite(MMC). In this study, TiNi alloy fiber was used to solve the problem of the tensile residual stress as the reinforced material. TiNi alloy fiber improves the tensile strength of composite by occurring compressive residual stress in matrix using shape memory effect of it. Pre-strain was added to generate compressive residual stress inside TiNi/A16061 shape memory alloy(SMA) composite. It was also evaluated the effect of compressive residual stress corresponding to pre-strains variation and volume fraction of TiNi alloy. AE technique was used to clarify the microscopic damage behavior at high temperature and the effect of pre-strain difference of TiNi/A16061 SMA composite. In addition, two dimensional AE source location technique was applied to inspect the crack initiation and propagation in composite.

• 대한기계학회논문집A
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• 제27권3호
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• pp.440-449
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• 2003

Residual strength of fiber metal laminates after impact was studied. 3/4 lay up FML was fabricated using 4 ply prepreg, 2 ply aluminum sheets, and 1 ply steel sheet. Quasi isotropic ([0/45/90/-45]s) and orthotropic ([0/90/0/90]s) FRP were also fabricated to compare with FML. Impact test were conducted by using instrumented drop weight impact machine (Dynatup, Model 8250). Penetration load and absorbed energy of FML were superior to those of FRPs. Tensile tests were conducted to evaluate the residual strength after impact. Strength degradation of FML was less than that of FRP. This means that the damage tolerance of FML is excellent than that of FRP. Residual strength of each specimen was predicted by using Whitney and Nuismer(WN) Model. Impact damage area is assumed as a circular notch in WN model. Damage width is defined as the average of back face and top face damage width of each specimen. Average stress and point stress criterions were used to calculate the characteristic length. It is supposing that a characteristic length is a constant. The distribution of characteristic length shows that the assumption is reasonable. Prediction was well matched with experiment under both stress criterions.