• Geomechanics and Engineering
• /
• 제13권6호
• /
• pp.977-995
• /
• 2017

It is well accepted that rock failure mechanism influence the cutting efficiency and determination of optimum cutting parameters. In this paper, an attempt was made to research the factors that affect the failure mechanism based on discrete element method (DEM). The influences of cutting depth, hydrostatic pressure, cutting velocity, back rake angle and joint set on failure mechanism in rock-cutting are researched by PFC2D. The results show that: the ductile failure occurs at shallow cutting depths, the brittle failure occurs as the depth of cut increases beyond a threshold value. The mean cutting forces have a linear related to the cutting depth if the cutting action is dominated by the ductile mode, however, the mean cutting forces are deviate from the linear relationship while the cutting action is dominated by the brittle mode. The failure mechanism changes from brittle mode with larger chips under atmospheric conditions, to ductile mode with crushed chips under hydrostatic conditions. As the cutting velocity increases, a grow number of micro-cracks are initiated around the cutter and the volume of the chipped fragmentation is decreasing correspondingly. The crack initiates and propagates parallel to the free surface with a smaller rake angle, but with the rake angle increases, the direction of crack initiation and propagation is changed to towards the intact rock. The existence of joint set have significant influence on crack initiation and propagation, it makes the crack prone to propagate along the joint.

• Structural Engineering and Mechanics
• /
• 제71권3호
• /
• pp.211-221
• /
• 2019

To study the eccentric compression behavior of ultra-high performance fiber reinforced concrete (UHPFRC) columns, six UHPFRC columns and one high-strength concrete (HSC) column were tested. Variation parameters include load eccentricity, volume of steel fibers and stirrup ratio. The crack pattern, failure mode, bearing capacity, and deformation of the specimens were studied. The results showed that the UHPFRC columns had different failure modes. The large eccentric compression failure mode was the longitudinal tensile reinforcements yielded and many horizontal cracks appeared in the tension zone. The small eccentric compression failure mode was the longitudinal compressive reinforcements yielded and vertical cracks appeared in the compressive zone. Because of the bridging effect of steel fibers, the number of cracks significantly increased, and the width of cracks decreased. The load-deflection curves of the UHPFRC columns showed gradually descending without sudden dropping, indicating that the specimens had better deformation. The finite element (FE) analysis was performed to stimulate the damage process of the specimens with monotonic loading. The concrete damaged plasticity (CDP) model was adopted to characterize the behaviour of UHPFRC. The contribution of the UHPFRC tensile strength was considered in the bearing capacity, and the theoretical calculation formulas were derived. The theoretical calculation results were consistent with the test results. This research can provide the experimental and theoretical basis for UHPFRC columns in engineering applications.

• Steel and Composite Structures
• /
• 제31권2호
• /
• pp.113-123
• /
• 2019

In this study, carbon fiber/epoxy (CF/EP) composites were interleaved with aramid nonwoven veils with an areal weight density of $8.5g/m^2$ to improve their Mode-I fracture toughness. The control and aramid interleaved CF/EP composite laminates were manufactured by VARTM in a [0]4 configuration. Tensile, three-point bending, compression, interlaminar shear, Charpy impact and Mode-I (DCB) fracture toughness values were determined to evaluate the effects of aramid nonwoven fabrics on the mechanical performance of the CF/EP composites. Thermomechanical behavior of the specimens was investigated by Dynamic Mechanical Analysis (DMA). The results showed that the propagation Mode-I fracture toughness values of CF/EP composites can be significantly improved (by about 72%) using aramid nonwoven fabrics. It was found that the main extrinsic toughening mechanism is aramid microfiber bridging acting behind the crack-tip. The incorporation of these nonwovens also increased interlaminar shear and Charpy impact strength by 10 and 16.5%, respectively. Moreover, it was revealed that the damping ability of the composites increased with the incorporation of aramid nonwoven fabrics in the interlaminar region of composites. On the other hand, they caused a reduction in in-plane mechanical properties due to the reduced carbon fiber volume fraction, increased thickness and void formation in the composites.

• 한국대기환경학회지
• /
• 제33권2호
• /
• pp.97-107
• /
• 2017

Columnar aerosol properties retrieved from solar radiation were investigated at the Yongin (YGN) SKYNET site over seven years from October 2008 to October 2015. Hourly averages were calculated when the data were available, and back trajectories were calculated to examine the effects of regional transport. Data recovery rate was low at 6.6%, primarily because solar radiation was measured only under daytime clear-sky conditions. Mean values of the fine-mode volume fraction (FMVF) as well as its seasonal variation were similar to those of $PM_{2.5}/PM_{10}$ although the coarse-mode fraction of column aerosols tended to be slightly larger. The values of single scattering albedo (SSA) and FMVF were lower in spring due to the effects of mineral dust, and higher in summer due to secondarily-formed inorganic ions. Back trajectories were grouped into five clusters according to the directions of transport paths. Aerosol loading was highest for Cluster 2 from the northwest, but SSA and FMVF were not particularly high or low because aerosols were composed of various materials with different properties. Aerosol loading was lowest for Cluster 5 from the Pacific Ocean passing through the south end of Japan, whose SSA and FMVF were highest as secondarily-formed inorganic ions were mixed.

• 한국분말재료학회지
• /
• 제11권6호
• /
• pp.528-534
• /
• 2004

Using the nano Fe powders having 50 nm in diameter, Fe compact bodies were fabricated by injec-tion molding process. The relationship between microstructure and material properties depending on the volume ratio of powder/binder and sintering temperature were characterized by SEM, TEM techniques. In the compact body with the volume percentage ratio of 45(Fe powder) : 55(binder), which was sintered at $700^{\circ}C,$ the relative density was about $97{\%},$ and the values of volume shrinkage and hardness were about $66.3{\%}$ and 242.0 Hv, respec-tively. Using the composition of 50(Fe powder) : 50(binder) and sintered at $700^{\circ}C,$ the values of relative density, volume shrinkage and hardness of Fe sintered bodies were $73.3{\%},\;47.6{\%}$ and 152.8 Hv, respectively. They showed brittle fracture mode due to the porous and fine microstructure.

• 한국음향학회지
• /
• 제22권1호
• /
• pp.69-77
• /
• 2003

연안역의 천해 해저면에 설치된 ADCP (Acoustic Doppler Current Profiler, 300㎑, 1200 ㎑)를 이용, 천해에서 체적 산란강도 (volume scattering strength, Sv)의 수직분포에 대한 시변동성을 알아보았다. 수심 85m와 113m에서 ADCP로 측정한 후방 산란강도의 일주기 변동성은 동물플랑크톤 (zooplankton)으로 추측되는 산란체의 일주기 수직이동 (daily vertical migration)에 기인된 것으로 추정되었다. 그러나 수심 20m의 천해에서 관측된 산란강도의 시변동성은 경험적 직교함수 (Empirical Orthogonal Function, EOF) 분석 결과, 해저면 부근의 변화가 천해 체적 산란강도의 변동성에 큰 영향을 주는 것으로 나타났다.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2005년도 제24회 춘계학술대회논문집
• /
• pp.219-224
• /
• 2005

본 연구는 CRW형식 무인항공기 추진시스템의 밸브 작동을 고려한 비행모드에 따른 천이성능특성을 파악하기 위해 SIMULINK를 이용하여 모델링 하였다. 주 엔진시스템의 천이모사에는 ICV 방법이 적용되였다. 그리고 밸브 시스템은 로터리 덕트와 메인 덕트로 빠져나가는 유량을 제어하는 시스템으로서 밸브를 통해 로터리 덕트로 빠져나가는 유량과 메인 덕트를 빠져나가는 유량이 합은 터빈의 출구 유량과 같다는 가정하에 수행 되었으며, 이때 밸브각 변화에 따른 손실, 유량 및 유효 면적 등이 고려되었다. 성능해석은 비행 천이 영역인 고도 1Km 비행 마하수 0.1에서 엔진최대회전수시 회전익 모드에서 고정익 모드로 변환시외 고정익 모드에서 회전익 모드로 변환 경우들이 수행되였다.

• 콘크리트학회논문집
• /
• 제25권5호
• /
• pp.573-581
• /
• 2013

이 논문은 강섬유보강콘크리트와 GFRP (glass fiber reinforced polymer)사이의 부착 특성을 조사하기 위한 실험적 연구를 수행하였다. 실험 주요 변수로는 보강근 지름, 섬유혼입량, 피복두께 및 콘크리트의 압축강도를 설정하였다. 부착파괴는 주로 콘크리트 피복에서의 쪼갬으로 인하여 유발되며, 이러한 콘크리트의 쪼갬파괴는 보강근과 콘크리트 사이의 변형 차이로 유발되는 인장력때문에 발생한다. 따라서, 보강근과 콘크리트 사이의 부착파괴를 방지하기 위하여, 콘크리트 피복부위의 인장강도를 향상시켜야 한다. 실험결과를 살펴보면, 섬유혼입량 증가는 부착강도를 크게 향상시키고 있으며, 피복두께는 최종 파괴모드를 변화시킴을 확인할 수 있었다. 보강근의 지름 또한 최종 파괴모드를 변화시킴을 확인할 수 있었다. 일반적으로 보강근의 지름은 부착특성에 영향을 미치는 것으로 알려져 있으나, 섬유혼입량은 부착특성에 큰 영향이 없는 것으로 알려져 있다. 콘크리트 압축강도의 증가는 보강근과 콘크리트 사이의 부착강도를 증가시켰으며, 이는 압축강도의 증가가 직접적으로 인장강도의 증가를 유발하기 때문이라고 판단된다.

• 대한방사선치료학회지
• /
• 제19권2호
• /
• pp.123-129
• /
• 2007

목 적: 전산화 단층촬영방법(Computed Tomography, CT)에 따라 고식적(Axial), 나선식(Helical), 연속(Cine) 주사방법으로 획득되어진 영상은 주사방법이 다르므로 각각의 재현되는 이미지 상에서 차이가 존재한다. 각각의 전산화 단층촬영 주사방법(scan type)이 움직임을 얼마나 정확히 묘사하는지 알아보고자 구동 팬톰을 이용하여 재현성에 대해 고찰해 보고자 한다. 대상 및 방법: 상 하 방향, 위 아래 방향 움직임을 재현하기 위해 자체 제작한 구동 팬톰과 호흡동조 구동 motor를 이용한다. 구동 motor 위에 표지자를 올려놓고 전산화 단층촬영 시 움직임을 구별하기 위해 표지자에 위치 표시를 위한 방사선 비투과성 물질(Localizer)을 부착한다. 자체 제작한 구동 팬톰을 이용하여 위 아래 움직임은 1.3 cm (16회/1분당)으로 고정 시키고, 호흡동조 구동 motor을 이용하여 상 하 움직임은 0.2 cm (8 rot/1분당)으로 고정 한다. 각각의 움직임을 고정 시키고 난 후, 전산화 단층 촬영 방법에 따라 고식적(Axial), 나선식(Helical), 연속(Cine) 주사방법으로 촬영한다. RPT 장비를 이용하여 움직임을 나타내는 표지자에 부착한 방사선 비투과성 물질과 볼륨 재현성이 정확한지 비교, 분석 한다. 결 과: 표지자의 전체 체적은 88.2 $cm^3$로 위 아래 방향 3 cm, 상 하 방향 0.3 cm 이동을 고려했을 때는 전체 체적이 184.3 $cm^3$이었다. 각각의 전산화 단층촬영방법에 따른 전체 체적은 고식적 주사방법에서는 135 $cm^3$, 나선식 주사방법에서는 164.9 $cm^3$, 연속 주사방법에서는 181.7 $cm^3$였다. 움직임에 대한 재현성을 나타내는 데 있어 연속 주사방법에서 가장 근접하게 표지자를 묘출하였다. 또한, 표지자에 부착한 방사선 비투과성 물질의 재현성에서도 연속 주사방법에서 가장 근접하게 나타내었다. 결 론: 전산화 단층촬영방법에 따른 고식적, 나선식, 연속 주사방법은 움직임에 영향을 많이 받는 장기를 촬영할 때, 움직임에 따른 정확한 장기 묘사 및 종양 조직의 움직임을 재현해야 한다. 본 실험에서 사용한 구동 팬톰을 이용한 표지자를 재현하는데 있어 전산화 단층촬영 시 연속 주사방법에서 촬영 할 때 가장 재현성이 높았다. 하지만, 임상 적용 시 환자의 호흡이나 움직임이 팬톰처럼 일정하지 않기 때문에 이를 위한 환자 교육 및 호흡을 일정하게 해줄 수 있는 장치의 사용 및 개발이 필요하며, 각각의 전산화 단층촬영방법에 대한 피폭선량에 대해서도 고려해야 할 것이라 사료 된다.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
• /
• pp.513-520
• /
• 2004

A steady-state/transient performance simulation model was newly developed for the propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) during flight mode transition. The CRW type UAV has a new concept RPV (Remotely Piloted Vehicle) which can fly at two flight modes such as the take-off/landing and low speed forward flight mode using the rotary wing driven by engine bypass exhaust gas and the high speed forward flight mode using the stopped wing and main engine thrust. The propulsion system of the CRW type UAV consists of the main engine system and the duct system. The flight vehicle may generally select a proper type and specific engine with acceptable thrust level to meet the flight mission in the propulsion system design phase. In this study, a turbojet engine with one spool was selected by decision of the vehicle system designer, and the duct system is composed of main duct, rotor duct, master valve, rotor tip-jet nozzles, and variable area main nozzle. In order to establish the safe flight mode transition region of the propulsion system, steady-state and transient performance simulation should be needed. Using this simulation model, the optimal fuel flow schedules were obtained to keep the proper surge margin and the turbine inlet temperature limitation through steady-state and transient performance estimation. Furthermore, these analysis results will be used to the control optimization of the propulsion system, later. In the transient performance model, ICV (Inter-Component Volume) model was used. The performance analysis using the developed models was performed at various flight conditions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the turbine inlet temperature overshoot limitation as well as the compressor surge margin. Because the engine performance simulation results without the duct system were well agreed with the engine manufacturer's data and the analysis results using a commercial program, it was confirmed that the validity of the proposed performance model was verified. However, the propulsion system performance model including the duct system will be compared with experimental measuring data, later.