• 한국해양공학회지
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• 제24권1호
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• pp.172-177
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• 2010

This study presents an explicit dynamic analysis of an adhesively bonded single-lap joint under an impact load. The finite element software, ANSYS LS-DYNA, was used for the analysis and Von Mises stresses were obtained from the analysis. To model the adherents, solid elements were used and a rigid body was assumed for impactor modeling. Three impact heights (1 m, 5 m, and 10 m) were applied to consider different impact conditions and infinite boundary conditions were applied to the end-area of each adherent to save computational time in the analysis. In addition to investigating the stresses in the normal state, we also investigated the stresses in a damaged state (elasticity deterioration), simulated by a change in Young's modulus for 36 of the 3600 elements in the upper layer of the adhesive. The results showed that the location of damage is critical to the stress state of each layer (upper, middle, and lower).

• International Journal of Naval Architecture and Ocean Engineering
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• 제11권1호
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• pp.233-243
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• 2019

In this paper, numerical and experimental studies are performed to investigate the liquid impact on a free falling wedge. In the numerical simulation, the structure is assumed to be rigid and the elastic response is ignored. The fully nonlinear coupling between wedge and water is considered by an auxiliary function method based on the Boundary Element Method (BEM). At the intersection of the wedge surface and liquid surface, two coincident nodes are used to decouple the boundary conditions. The Eulerian free surface conditions in the local coordinate system are adopted to update the deformed free surface. In the experiments, five pressure sensors are fixed on each side of the wedge which is released from an experimental installation. Steel and aluminum wedges that have different structural elasticity are used in the experiments to investigate the influence of structural elasticity on the impact force. Numerical results are compared with experimental data and they agree very well. The influence of fluid gravity, body mass, initial entry speed and deadrise angle on the impact pressure are further investigated.

• 한국멀티미디어학회논문지
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• 제21권7호
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• pp.787-794
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• 2018

We propose a new framework which expresses the mist and scratches of cracked ice by an impact. We combine the grid projection technique, boundary particles method, and level-set method commonly used in fluid simulations to determine the region on the surface of an ice object which is affected by a collision. Mist is then generated in proportion to the impact, and immediately diffused, using a geodesic distance field to limit dissipation. The gradient of the mist is subsequently used to create realistic patterns of scratches and elongated air bubbles. Cracks of the ice object can also be considered, and the density of the mist made to vary realistically between fragments. As a result, our method not only represents high-quality ice effects, but also allows easy integration into existing rigid body simulation solvers.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2008년도 추계학술대회A
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• pp.706-710
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• 2008

The experiment of dome port cover under shock impact is performed with shock tube. The dome port cover blocked intake air duct up from the solid propellant during air breathing vehicle speed reach Mach 2.0. When the air breathing vehicle reach Mach 2.0, the inlet cover is removed and the dome port cover is broken to pieces by detonator or pressure of inlet air. Thus the dome port cover not only must stand the pressure of combustion chamber but also easy to break from the RAM pressure. In this study, a fracture evaluation on the $Al_2O_3$ ceramic spherical dome and circular plate port under impact has been presented. Ceramic were supported by the rigid body and a couple of O-ring. The Mooney-Rivlin model have been used to describe behaviors of both O-ring. And spherical dome and circular plate fracture results of the LS-DYNA code using Johnson-Holmquist(JH-2) constitutive equation was compared.

• 한국유체기계학회 논문집
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• 제18권6호
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• pp.5-11
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• 2015

In a pressurized water reactor (PWR), control rod assembly (CRA) falls into the guide tubes of a fuel assembly due to gravity for scram. Various theoretical approaches and numerical analyses have been performed because its shape is simple and its design was completely developed several decades ago. A control rod assembly for a sodium-cooled faster reactor (SFR) which is geometrically more complicated is being actively developed in Korea nowadays. Drop time and impact velocity of a CRA are important parameters with respect to reactivity insertion time and the mechanical robustness of a CRA and a guide duct. In this paper, computational method considering simultaneously the equation of motion for rigid body and the Navier-Stokes equations for fluid is suggested and verified by comparison with theoretical analysis results. Through this valuable CFD analysis method, drop time and impact velocity of initially designed SFR CRA are evaluated before performing scram tests with it.

• 대한교통학회지
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• 제18권4호
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• pp.107-115
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• 2000

본 논문에서는 자동차 충돌사고 재구성에 직접 적용이 가능하도록, 주어지는 두 차량의 충돌후 속도, 차량에 관한 간단한 물성치와 기하학적 상대 위치들에 근거하여 충돌 직전 속도 성분들을 계산하는 소위 충돌 거동에 대한 역해석 방법을 제시한다. 또한, 제시하는 역해석 방법이 실용적 의미를 가지게 하기 위해서, 충돌 후 조건들로부터 반발계수와 역적비에 대한 적절한 추정 방법과 더불어 충돌 변형으로부터 유추할 수 있는 충돌 과정동안의 에너지 손실에 근거한 역해석 방안도 포함한다. 실차충돌 실험자료의 분석 결과에 따르면, 역적-운동량이론에만 근거한 역해석 결과뿐만 아니라 에너지 손실에 근거한 역해석 결과도 실험 결과와 좋은 일치를 보여주고 있다 강체역학의 범주내에서 역해석을 수행할 수 없는 공통속도 조건과 같은 경우나 반발계수에 관한 추정결과가 적절하지 않게 되는 등 단지 역적-운동량이론만을 이용한 해석 결과가 미흡한 경우에는 에너지 손실에 근거한 역해석 방법을 보완적으로 활용할 수 있을 것이다. 본 논문에서 제시한 충돌 과정 역해석 결과는 자동차충돌 해석 결과 및 충돌 전·후 거동에 대한 역미끄럼 해석 결과와 유기적으로 결합하여 자동차 충돌 사고 전 과정에 대한 직접적인 역해석을 수행할 수 있는 사고 재구성 패키지의 개발을 기대할 수 있다.

• International Journal of Precision Engineering and Manufacturing
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• 제9권4호
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• pp.22-25
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• 2008

The dynamic response of the head arm assembly (HAA) of a hard disk drive to an impact load was obtained from a 3D non-linear finite element model using ANSYS/LS-DYNA and from experiments using a modified levitation mass method (LMM). In the finite element model, the impact load was created by modeling the mass as a rigid body and making it collide with the HAA. The velocity, displacement, acceleration, and inertial force of the mass were then obtained from the time history data of the finite element analysis. In the LMM, a mass that was levitated with an aerostatic linear bearing, and hence encountered negligible friction, was made to collide with the actuator arm, resulting in a dynamic bending test for the arm. During the collision, the Doppler frequency shift of the laser beam reflected from the mass was accurately measured with an optical interferometer. The velocity, displacement, acceleration, and inertial force of the mass were accurately calculated from the measured time-varying Doppler frequency shift. A good correlation between the experimental data and FEA results was observed. The FEA was also used to investigate the dynamic response of the HAA to impact by different masses.

• International Journal of Aeronautical and Space Sciences
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• 제16권3호
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• pp.394-406
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• 2015

In this work, an efficient aircraft landing simulation strategy is proposed to develop an efficient and reliable hard-landing monitoring procedure. Landing stage is the most dangerous moment during operation cycle of aircraft and it may cause structural damage when hard-landing occurs. Therefore, the occurrence of hard-landing should be reported accurately to guarantee the structural integrity of aircraft. In order to accurately determine whether hard-landing occurs or not from given landing conditions, full nonlinear structural dynamic simulation can be performed, but this approach is highly time-consuming. Thus, a more efficient approach for aircraft landing simulation which uses a hierarchical aircraft landing model and an extended inertia relief technique is proposed. The proposed aircraft landing model is composed of a multi-body dynamics model equipped with landing gear and tire models to extract the impact force and inertia force at touch-down and a linear dynamic structural model with an extended inertia relief method to analyze the structural response subject to the prescribed rigid body motion and the forces extracted from the multi-body dynamics model. The numerical examples show the efficiency and practical advantages of the proposed landing model as an essential component of aircraft hard-landing monitoring procedure.

• 한국전산구조공학회:학술대회논문집
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• 한국전산구조공학회 1994년도 가을 학술발표회 논문집
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• pp.183-190
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• 1994

The paper provides a review of the analysis methods currently being used to perform seismic analysis of free standing high density spent fuel storage racks for PWR. On the basis of the analysis techniques obtained by KAERI from the design experience of Yonggwang unit 3&4 and Ulchin unit 3&4, the analysis procedure and modeling methods are discussed. The analysis of free standing fuel racks requires consideration of complex phenomena such as hydrodynamic coupling, impact through gap between fuel assembly and poison box and racks, frictional effect, rigid body sliding and tipping and etc. The present modeling of these factors is reviewed in comparison with the recommendation of regulatory group. Further improvement of analysis method and the current issues for the development are discussed.

• Composites Research
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• 제21권2호
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• pp.15-24
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• 2008

본 연구에서는 Kevlar 직물에 전단농화 특성을 갖는 나노 실리카 입자를 함침시켜 저속충격 특성 및 마찰특성 실험을 수행하였다. 나노입자의 크기에 따른 영향력을 평가하기 위해 100nm, 300nm, 500nm 직경크기의 구형 실리카 입자를 충진한 전단농화유체를 제작하였으며 유변물성 시험을 통해 전단담화 현상 및 급격히 점성이 증가하는 전단농화현상을 확인하였다. 전단농화유체를 Kevlar 직물에 함침시켜 저속 낙하 충격시험을 수행한 결과 나노입자 처리를 한 Kevlar 직물에서 우수한 충격흡수 특성을 보였으며 특히 함침된 나노입자의 크기가 작을수록 충격흡수양이 증가하였고 변형의 양도 가장 적게 나타났다. Kevlar 직물 내에서의 얀의 Pull-out 실험과 직물간 마찰력 실험을 통해 나노입자의 크기가 작을수록 전단농화 현상으로 인한 마찰력의 증가가 더욱 크게 나타남을 확인하였다. 이러한 마찰력의 증가가 얀의 Pull-out 에너지를 증가시키게 되어 주요 충격흡수 메커니즘으로 작용하게 되는 것이다.