• Journal of Welding and Joining
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• v.22 no.4
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• pp.4-6
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• 2004

기계부품이나 구조물의 파손사고 시에 우선 조사하여야 할 것은 파면상태이다. 파면에는 그 파손발생의 초기부터 최종 파단에 이르기까지의 모든 경과가 나타나 있고, 경험을 통하여 파면으로부터 파괴의 흐름을 읽을 수 있다. 파괴된 부품의 파면을 육안 혹은 20배 이하의 저배율로 조사하면, 일반적으로 명료한 형상이 관찰된다.(중략)

• Composites Research
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• v.30 no.6
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• pp.384-392
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• 2017

Sandwich panels with three different joint configurations were tested to design a novel sandwich joint structure that can effectively support both the tensile and compressive loads. The sandwich core was mainly aluminum flex honeycomb but the PMI foam core was limitedly applied to the ramp area which is transition part from sandwich to solid laminate. The face of sandwich panel was made of carbon fiber composite. For configuration 1, the composite flange and the sandwich panel were cocured. For configurations 2 and 3, an aluminum flange was fastened to the solid laminate by HI-LOK pins and adhesive. The average compressive failure loads of configurations 1, 2, and 3 were 295, 226, and 291 kN, respectively, and the average tensile failure loads were 47.3 (delamination), 83.7 (bolt failure), and 291 (fixture damage) kN, respectively. Considering the compressive failure loads only, both the configurations 1 and 3 showed good performance. However, the configuration 1 showed delamination in the corner of the composite flange under tension at early stage of loading. Therefore, it was confirmed that the structure that can effectively support tension and compressive loads at the same time is the configuration 3 which used a mechanically fastened aluminum flange so that there is no risk of delamination at the corner.

• Composites Research
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• v.29 no.4
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• pp.209-215
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• 2016

The failure of composite sandwich structures with thickness and material variation was studied. The main body of the structure is sandwich plate made of the carbon composite face and Aluminum honeycomb core. It is connected with composite laminated flange without core through transition region of tapered sandwich panel with foam core. Tension and compression tests were conducted for the total of 6 panels, 3 for each. Test results showed that the panels under compression are vulnerable to the face failure along the material discontinuity line between two different cores. However the failure load of which panel does not show such failure can carry 16% more load and fails in honeycomb core and face debonding. For the tensile load, the extensive delamination failure was observed at the corner radius which connects the panel and the flange. The average failure load for compression is about 7 times the tensile failure load. Accordingly, these sandwich structures should be applied to the components that endure the compressive loadings.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.23 no.11 s.170
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• pp.2096-2101
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• 1999

This paper presents the effect of shape of external corrosion in pipeline on failure prediction by using numerical simulation. The numerical study for the pipeline failure analysis is based on the FEM(Finite Element Method) with an elastic-plastic and large-deformation analysis. The predicted failure stress assessed for the simulated corrosion defects having different corroded shapes along the pipeline axis are compared with those by methods specified in ANSl/ASME B31G code and a modified B31G code.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.3
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• pp.37-43
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• 2006

Six types of hat stiffened composite panels were manufactured with different bonding methods and stiffener section shapes and compression testing of these panels were performed. The panels showed similar behaviors in bucking and postbuckling region before a skin-stiffener separation failure occurred. Although all the separation failures occurred at the same locations of stiffener flanges close by skin buckling crests, the separation loads, separation failure growth behaviors and final collapse loads were different with respect to bonding methods and stiffener section shapes. As the separation failure initiated early and propagated larger area, collapse loads and structural efficiency of the panels decreased.

• Composites Research
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• v.22 no.5
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• pp.30-36
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• 2009

The failure strengths and modes in carbon fiber reinforced polymeric composites, with two serial bolt-fastened composite joints, were investigated to evaluate the typical joint configurations of composite components. The parametric studies were performed experimentally at room temperature dry and elevated temperature wet, $82.2^{\circ}C$ on several different laminate configurations. Based on the experimental data presented, two basic load-displacements curves are observed. Each failure mode has the characteristic curve. It is showed that the bearing failure mode occurs in elevated temperature wet condition. It is analysed that the strength of bearing failure mode is not highly depending on the effective modulus of specimen. The failure strength at elevated temperature wet is decreased by the cause of interfacial deterioration between fiber and matrix with moisture absorption.

• Proceedings of the Korean Vacuum Society Conference
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• 2015.08a
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• pp.93.2-93.2
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• 2015

플라즈마를 포함한 반응성 가스 공정 분석용 사중극자 질량분석기의 필라멘트의 파손양상을 조사하였다. 또한 유전체 증착층이 이온원 성능에 미치는 영향을 분석하기 위하여 이온원의 일반적인 가동 전압 조건에서 Poisson방정식을 이용하여 전위를 수치 해석으로 구하였다. 사용중 파손된 필라멘트의 파단면을 주사전자현미경으로 관찰결과, 수직으로 절단되는 양상과 직경이 점차 작아지면서 erosion되는 두가지 양상을 보였다. 또한 파단면은 표면균열과 패시팅(faceting) 현상을 보였다. 필라멘트 사용시 가장 큰 문제는 패시팅(faceting)이다. 대부분의 결정에서는 다른 결정면보다 에너지 준위가 낮은 결정면이 존재한다. W 원자는 고온에서 확산 또는 증발하여 표면에서 다시 응축할 때 표면 에너지를 최소화하기 위한 독특한 평형 형상이 만들어 지는데 이것이 패시팅의 구동력이다. 이때 국부적으로 단면적이 감소하는 곳이 생기는데, 이 지점이 집중적으로 가열되고 증발이 가속화하여 파손된다. 파단면을 EDS 분석결과, 산화물을 포함한 F, Fe 및 C이 검출되었다. 이 F과 C는 공정중 사용된 CF4의 분해에 의한 것으로 생각되며, 파손된 필라멘트를 Ar 유도결합 플라즈마로 처리한 결과 이 F, Fe 및 C의 양이 감소하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.10
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• pp.806-813
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• 2018

The fracture of a turbine blade of aerospace engine is presented. Although there are a lot of causes and failure modes in blades, the main failure modes are two ways that fracture and fatigue. Degradation of blade material affects most failure modes. Total propagation of failure in this study specifies failure of fracture type. Some section appears fatigue mode. Especially since this study describes analysis of failure for blade in high temperature, it can be a case in point. Analysed blade is Ni super alloy. Investigations of blade are visual inspection, material, microstructure, high temperature stress rupture creep test, analysis and fracture surface, etc. The root cause for fracture was stress rupture due to abnormal thermal environment. Thermal property of Ni super alloy is excellent but if each chemical composition of alloys are different due to change mechanical properties, selection of material is very important.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.38 no.8
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• pp.917-923
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• 2014

Subminiature joining bolts are required for the electronic parts of gadgets such as mobile phones and watch phones. During the miniaturization of bolt heads, it is difficult to obtain sufficient joining force owing to the risk of shear fracture of the bolt head or severe plastic deformation on the bit region. In this study, the maximum joining torque for the bit depth was predicted using finite element analysis. A shear fracture test was conducted on a wire used in bolt forming. The results of this test were subjected to finite element analysis and a fracture criterion was obtained by comparing the experimental and analysis results. The shear fracture of the bolt head during joining was predicted based on the obtained criterion. Furthermore, the maximum joining torque was predicted for various bit depths. Fracture on the boundary between the bolt head and thread was found to occur in lower joining torque as bit depth increases.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.1
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• pp.65-74
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• 2002

Composite materials are used for main structural components of aircraft fuselage such as skin, stringer and frame to reduce weight. Failure and buckling analysis of the composite fuselage components have been done for structural design. The loads of MD90-30 are applied to each component. Various shapes of section such as I, Z and T-type are chosen as candidate composite stringer and frame. The analysis results of composite fuselage components are compared according to ply-angle and ply-number, and the section type. The numerical results shows that ply-angle and ply-number have important effects on failure caused by axial load for the frame are important design parameters of composite fuselage components. This study suggests several design tips for composite fuselage components.