Recently, the light weight and the safety of automobile are the important targets of automotive design and the parts for car have been substituted the plastic or the porous material for the steel material. As the aluminium foam has many pores at its surface, it has the fatigue property of bonded face which differs from general material. In this study, two dimensional model is designed and performed with the fatigue analysis as the variable(θ value) becomes the slant angle of bonded face at the specimen with the aluminium foam. As the analysis result on the models with the slant angles of 6°, 8° and 10°, the bonding forces are disappeared when the fatigue loads are repeated during 4000 cycle, 4500cycle and 5000cycle respectively. By comparing with the analysis results of three models, the fatigue cycle to endure fatigue load becomes larger as the slant bonded angle becomes higher. So, the structural safety can be seen by applying only as only a simulation of finite element method instead of the experiment where much cost and time is spent. In this study, the configuration of aluminum foam is designed with the shape of TDCB Mode II. The shear fatigue strength of the bonded structure can be evaluated by the analysis program of ANSYS.

투명 전도성 산화물로서 알루미늄과 붕소가 함께 도핑된 아연산화물(AZOB)이 900℃에서 분무 열분해법에 의해 제조되었다. 얻어진 마이크론 크기의 AZOB 분말은 알루미늄, 붕소 및 아연의 수용액으로부터 얻어진다. 분무 열분해로 얻어진 마이크론 크기의 AZOB 분말은 700℃에서 두 시간동안의 후 소성 과정과 24 시간 동안의 볼 밀링을 통해 나노 크기의 AZOB으로 변환된다. AZOB을 구성하는 일차 입자의 크기를 Debye-Scherrer 식에 의해 계산하였고 압축된 AZOB 펠렛의 표면 저항을 측정하였다.

Nowadays, the automotive industry has target to improve the fuel consumption due to restricted exhaust gas regulation. For this reason, the applicability of lightweight material, Al alloys, Mg alloys are also being expanded. In this concept, high strength steel, DP780 and light alloy, AL5052 are joined in the right place of the car body. However, it is difficult to join to steel and aluminum by conventional fusion welding. Generally, in respect to dissimilar metal joining by fusion welding, intermetallic compound layer formed at joint interface; hot cracking in generated. To evaluate the welding quality, tensile test and metallographic examination was carried. Especially, correlation between Heat per unit length and formation of intermetallic compound layer was minutely analyzed. Finally, optimal welding condition was selected for improvement of strength at weldment and practical use.

In this study, the specimen of tapered double cantilever beam(TDCB) with aluminum foam is designed and shearing fatigue strength is based on the investigation of static behaviour analysis under the condition of mode Ⅱ. These specimen models have length and width of 200 mm and 25 mm. The inclined angles of adhesive face at the specimens are 6°, 8 °and 10°. As the inclined angle becomes higher, the time for which the model can not be broken during fatigue load becomes longer. The shearing strength of TDCB bonded structure with aluminum foam applied by shearing fatigue load can be evaluated through finite element method.

In this study, the weldability of ADC12 FSW joints obtained by the load control type of the FSW machine is examined. The higher the tool plunge downforce the wider the range of the optimum FSW conditions is obtained. However, there is a limit of optimum range with increasing the tool plunge downforces. The three different types of defects are formed in ADC12 FSW joints, depending on the welding conditions. One is a large mass of flash due to the excess heat input, another is a cavity or groove-like defects caused by insufficient heat input and the other is a cavity caused by the abnormal stirring. As for the abnormal stirring, it is very clearly seen that the shape of the top part on the advancing side in the stir zone is completely different. For this type of defect, the effect of the tool plunge downforce is not significant, though the size of the defect due to insufficient heat input significantly is decreased with the increasing downforce

In this study, tapered double cantilever beam bonded with aluminum foam composite is modelled and analyzed by finite element analysis. The bonding strength on Mode II of this structure is evaluated and investigated. In cases of inclined angles of 6°, 8° and 10°, maximum equivalent stresses occur 1.29, 1.59 and 2.6 MPa respectively at the range of forced displacement of 5 to 6 mm. And maximum reaction forces become 186, 208 and 235 N individually at this range of displacement in these cases. By the analysis result on 3 kinds of models, the maximum reaction load increases as angle of inclination of model increases. And the elapsed time to approach the maximum load and the time to disappear away become shorter. This study result can be applied into the real composite structure with aluminum foam in case that the surface bonded with adhesive is inclined. This fracture behavior can also be investigated and the impact property can be examined

This study is research on the thermal emissivity depending on the alignment degrees of graphite flakes. Samples were manufactured by a slurry of natural graphite flakes with organic binder and subsequent dip-coating on an aluminum substrate. The alignment degrees were controlled by applying magnetic field strength (0, 1, and 3 kG) to the coated samples. The alignment degree of the sample was measured by XRD. The thermal emissivity was measured by an infrared thermal image camera at 100˚C. The alignment degrees were 0.04, 0.11, and 0.17 and the applied magnetic field strengths were 0, 1, and 3 kG, respectively. The thermal emissivities were 0.829, 0.837, and 0.844 and the applying magnetic field strengths were 0, 1, and 3 kG, respectively. In this study the correlation coefficient, R2, between thermal emissivity and alignment degree was 0.997. Therefore, it was concluded that the thermal emissivities are correlated with the alignment degree of the graphite flakes.

차량, 수송, 조선 등 많은 산업이 발전함에 따라 기계장치를 구성하고 있는 각종 재료의 특성 또한 날로 발전하고 있다. 과거 단순 강만 사용하여 기계를 설계하던 것과 달리 현재는 특수합금강과 복합재료를 사용하여 기계의 성능을 향상시키고 있다. 이처럼 많은 산업 분야에서 재료의 특성을 파악하여 적시 적소에 사용하여 기계를 설계하는 것은 기계설계자들에게 매우 중요한 과제가 되었다. 본 논문에서는 알루미늄 폼 복합재료로 된 TDCB(이중외팔보) 시험편의 파괴 거동을 시뮬레이션 해석과 실험 검증하였다. 실험과 해석에 사용된 모델은 영국 공업규격과 ISO국제규격에 의거한 3D 형태로 하였다. θ=12°일 때의 해석 결과로 한쪽 Beam이 일정한 속도로 이동하면서 접착력에 대한 반력이 발생하는데 Beam이 약 5mm 이동하였을 때 약 270N의 최대 반력이 나타나는 것을 볼 수 있다. 본 연구에서는 실험과 유한요소법을 통한 비교분석으로 물성데이터를 확보하고, 실험결과와 해석결과의 유사성을 검증하여 보다 쉽고 빠른 소재의 특성을 파악하는 방법을 검증해 보았다.

Britsh StandardBS 7991)에 명시된 DCB 시험편을 본 연구에 맞게 수정 후 두께 25mm, 35mm, 45mm, 55mm, 그리고 65mm의 DCB시험편을 제작하였다. 이 후 시험편을 Single-lap 방식으로 접착한 후 정적실험에서 도출된 최대 전단력을 각 시험편에 10Hz로 피로하중을 가하였다. 실험 결과값에 대한 수치해석적 검증을 하고자 상용 해석 프로그램인 ANSYS를 통해 실험과 동일한 시험편과 조건 하에 해석을 수행하였다. 접착력 해석을 하기 위해서 Mesh의 절점(node)들의 관계가 매우 중요하기 때문에 접착된 부분의 모든 절점들은 동일 선상에 있게 Mesh를 형성하였다. 실험 결과와 해석 결과를 비교해 본 결과 피로하중이 약 200cycle 반복되었을 때 최대 등가응력이 발생 하였고, 이때 전단방향으로 변위가 약 11mm 진전 된 것을 볼 수 있었다. 이후 4000cycle가량 피로하중이 반복 될 동안 변위는 일정하게 점점 증가한 후 피로하중이 약 4800cycle 반복 되었을 때 실험과 해석 데이터 모두 접착계면에서 완전한 전단 파괴가 일어난 것을 볼 수 있었다. 이때 변위는 약 20mm 진행 되었다. 해석을 통해 실험 데이터를 검증해 본 결과 두 결과 값은 완전 하게 같지는 않지만 유한요소법 해석 결과에 대한 신뢰를 확보 할 수 있었다. 이는 실제 구조물에 실험 없이 간단한 재료 물성치만으로도 해석을 통하여 구조적 안전성을 알아 볼 수 있는 한 방법이 될 수 있을 것이라고 사료된다.

Adhesive joint method has been used instead of welding, reveted joint, bolt and nut in various industry fields recently. Aluminum foam has hole or crack on adhesive interface which is different from common composite material. To investigate shear characteristic of adhesive interface between aluminum foams, double cantilever beams(DCB) with thicknesses of 25mm, 45mm and 65mm bonded with single-lab joints are designed. The relation between nodes at finite element model is important to investigate adhesive strength in this study. All meshes are generated and some nodes are located on adhesive zone along collinear axis. As reaction force obtained by static experiment is applied, fatigue analysis is carried with 10Hz. In advance, adhesive property is obtained by preliminary experiment for applying adhesive strength to input into simulation analysis. With these conditions, the analysis results show that 2.97MPa, 3.10MPa and 4.2MPa of maximum equivalent stresses are shown respectively in case model thicknesses are 25mm, 45mm and 65mm. By use of the simulation result at this study, it is possible to find adhesive behavior of aluminum foam and be applied to real adhesive joint structure without experiment by sparing experimental cost and time

In this study, simulation analyses on the impact property of aluminum foam are carried and verified by experimental results. When aluminum foams with thicknesses of 25mm and 35mm are applied by impact energy of 14J, impact energy and deformation happened at aluminum foam are investigated by comparing experimental and analysis results. Experimental and analysis results of deformations or absorbed impact energy become similar each other. After verifying these simulation results with experimental results, impact properties of aluminum foams with thicknesses of 45mm and 55mm are also investigated by simulation results. As impact properties of aluminum foam can be studied effectively through only simulation results, it is thought to spare much time and cost by investigating various impact properties of aluminum foams with simulation analysis.

This study aims to evaluate structural safety through FEM on the hollow shaft and the shaft filled with aluminum foam as the impact beam made of high tensile strength steel, Force reactions of impact beams are investigated when the forced displacement of 50mm is applied equally on two beams. When impact velocity of 80km/h is applied onto impact beams equally with the limit velocity of automobile on national road, how much impact energies can be absorbed by beams are also investigated. As study result, impact beams without aluminum foam and with aluminum foam show the maximum reaction forces of 15.53kN and 20.34kN respectively in case of the forced displacement of 50mm. As impact analysis result, impact beams without aluminum foam and with aluminum foam can absorb impact energies of 560J and 820J respectively. As impact beam with aluminum foam has reaction force and impact energy more than 23% and 30% than without aluminum foam, impact beam with aluminum foam has more safety than without aluminum foam.

알루미늄 폼을 볼트나 너트를 이용하여 체결한다면 경량성이 감소되므로 접착제로 접합하는 것이 가 장 효율적이다. 이런 알루미늄 폼 접착 구조물에 대한 충격 피로 특성과 접착 합면에 대한 파괴인성 연 구는 매우 부족하며 또한 중요하다. 이에 따라 본 연구에서는 알루미늄 폼으로 만들어진 DCB모델을 접 착제로 접합한 후 두께를 변수로 하여 25mm 부터 45mm까지 10mm차이를 두어 실험과 컴퓨터 시뮬레 이션을 통하여 수행하였다. 실험은 MTS사의 인장 시험기를 사용하여 강제 변위 100mm를 주어 변위에 따른 전단력을 알아보았고, 실험과 똑같은 조건하에 ANSYS를 이용하여 유한요소해석을 수행하였다. 실험과 유한요소해석 값을 비교하여 접착제로 접합된 알루미늄 폼 구조물의 접착 합면에 대한 파괴인성을 고찰하였다.

이중외팔보 모델은 일반적으로 복합재료의 구조테스트와 접착 접합의 테스트에 많이 쓰인다. 본 연구 에서 쓰인 재료는 알루미늄 합금2014이다. 또한 접착 구조물의 접착 면에서 발생한 에너지 해방율 및 유한요소해석을 통하여 알루미늄의 충격에 대한 기계적 특성을 알고자 하는 것이 목적에 있다. 상단부와 하단부의 접착 부위는 하중 점으로부터 100mm 떨어지도록 예비크랙을 두어 접착을 하도록 설계하였다. 하중은 핀에 Y축 방향으로 작용하였다. 충격속도는 7. 5m/s와 12.5m/s로 가하였다. 충격속도가 12.5m/s 일 때의 에너지 해방율은 약 7500J/m2으로 나왔다. 충격 속도가 빠를수록 하중 핀에 가해지는 하중이 증가된다는 것을 알 수 있었으며, 에너지 해방율도 높게 나타나는 것을 알 수 있었다.

본 연구는 알루미늄 폼 복합재료로 접합된 TDCB 모델에 대해 구조적 시뮬레이션 해석을 하였다. 이 해석을 통하여 등가응력, 변형 에너지 및 접착부의 압력에 대한 자료를 얻었다. 또한 실험을 하여 해석 자료에 대한 검증을 하였다. 본 연구의 자료를 통해 알루미늄 폼 재질로 접합된 실제 복합재 구조물에 적용시켜 파괴거동을 분석하고 그 기계적인 특성을 파악할 수 있다.

Aluminum foam has many superb properties such as light weight, impact absorption and thermal resistance by comparing with original metallic materials. Composite materials made of aluminum foam have used at various fields as automotive bumper, shock absorption, vessel and aircraft. But it is inefficient to join aluminum foam with bolt and nut because of the property of light weight. In this study, this approach is investigated by joining aluminum foam with adhesive. Impact fatigue and failure toughness at the commissure of adhesive structure are studied by simulation analysis. This study aims to investigate the shear strength evaluation at shear mode of adhesively bonded joint with double cantilever beam(DCB) made of aluminum foam.

New material which absorbs impact energy effectively and has excellent mechanical property is developed. The used amount is increased at automobile field day by day. Aluminum foam with various air sell lattices within is one of representative porosity metals which are used at many automobile parts because it has the excellent lightness and impact energy absorption function. For this reason, aluminum foam is used widely as a component among composite materials. This study aims to investigate systematically the mechanical property of foam through computer simulation. In order to obtain the property of aluminum foam, aluminum foam is designed as the dimension of 100mm × 100mm × 25mm and the striker that has the diameter of 12.5mm is supposed to impact aluminum foam with impact energies of 6J, 10J, and 14J. Aluminum foam is not penetrated when striker given by energy of 6J or 10J impacts into it, but aluminum foam is penetrated by striker in case of impact energy of 14J. The result can provide the basic data in order to develop the advanced composite material.

four kinds of models designed by the basis of British industrial standard and ISO international standard in this study. Energy release rates at mode 1 are investigated by the fatigue analysis of aluminum foam TDCB model bonded with adhesive. These analysis models are compared each other by classifying four models into m values with 2, 2.5, 3 and 3.5. The value of m as the gradient of model is represented with the function of crack length(a) and height of model(h). Through the correlation relation, the fracture behavior of bonded material is analyzed and these analysis results can be applied to composite structures of various areas. Mechanical property and fracture toughness of composite material are also analyzed in this study.

The mechanical properties and microstructures of aluminum-matrix composites fabricated by the dispersion of fine alumina particles less than 20μm in size into 6061 aluminum alloys are investigated in this study. In the as-quenched state, the yield stress of the composite is 40~85 MPa higher than that of the 6061 alloy. This difference is attributed to the high density of dislocations within the matrix introduced due to the difference in the thermal expansion coefficients between the matrix and the reinforcement. The difference in the yield stress between the composite and the 6061 alloy decreases with the aging time and the age-hardening curves of both materials show a similar trend. At room temperature, the strain-hardening rate of the composite is higher than that of the 6061 alloy, most likely because the distribution of reinforcements enhances the dislocation density during deformation. Both the yield stress and the strain-hardening rate of the T6-treated composite decrease as the testing temperature increases, and the rate of decrease is faster in the composite than in the 6061 alloy. Under creep conditions, the stress exponents of the T6-treated composite vary from 8.3 at 473 K to 4.8 at 623 K. These exponents are larger than those of the 6061 matrix alloy.