• 한국전산유체공학회지
• /
• 제14권3호
• /
• pp.33-48
• /
• 2009

In the present study, a fast grid deformation technique has been incorporated into the unsteady compressible and incompressible viscous flow solvers on unstructured hybrid meshes. An algebraic method based on the basis decomposition of normal edge vector was used for the deformation of viscous elements, and a ball-vertex spring analogy was adopted for inviscid elements among several spring analogy methods due to its robustness. The present method was validated by comparing the results obtained from the grid deformation and the rigid motion of entire grids. Fish swimming motion of an NACA0012 airfoil and flapping wing motion of a generic fighter were also simulated to demonstrate the robustness of the present grid deformation technique.

• 한국항공우주학회지
• /
• 제32권8호
• /
• pp.91-100
• /
• 2004

경사기능재료 판에 대한 열탄성 변형과 응력 해석을 위해 Green 함수 방법이 채택되었다. 3 차원 비정상 온도분포에 대한 해는 적층판 이론에 의해 얻어진다. 열탄성 문제에 대한 기본 방정식은 각각 평면외 (out-plane) 변형과 평면내 (in-plane) 힘에 의해 유도되었다. 굽힘과 평면내 힘에 의한 열탄성 변형과 응력분포는 Galerkin 방법에 근거한 Green 함수를 이용하여 해석하였다. 열탄성 변형과 응력분포 해석을 위한 Galerkin Green 함수의 특성함수들은 사각판의 제차 경계조건을 만족시키는 허용함수들의 급수 형태로 근사화되었다. 단수지시된 사각 판에 대한 수치해석이 수행되었으며, 정사기능재료의 물성치가 판의 비정상 열탄성 거동에 미치는 영향이 검토되었다.

• 한국주조공학회지
• /
• 제13권1호
• /
• pp.81-93
• /
• 1993

It is well-known that the analysis of elasto-plastic thermal stress and deformation are substantially important in optimal design of metal casting mould. The unsteady state thermal stress and deformation generated during the solidification process of ingot and mould have been analyzed by two dimensional thermal elasto-plastic theories. Distributions of temperature, stress and relative displacement of the mould are calculated by the finite element method and compared with experimental results. In the elasto-plastic thermal stress analysis, compressive stress occurred at the inside wall of the mould whereas tensile stress occurred at outside wall. A coincidence between the analytical and experimental results is found to be fairly good, showing that the proposed analytical method is reliable.

• Journal of Mechanical Science and Technology
• /
• 제20권4호
• /
• pp.533-544
• /
• 2006

The amplitude and phase lag of surface deformation were determined for a compliant coating under the action of turbulent pressure fluctuations. For this purpose, pressure fluctuations were measured experimentally. The amplitude and duration of coherent wave train of pressure fluctuations were investigated using digital filtration. The transient response was calculated for stabilization of forced oscillations of the coating in approximation of local deformation. The response of coating was analyzed with considerations of its inertial properties and limited duration of coherent harmonics action of pressure fluctuations. It is shown that a compliant coating interacts not with the whole spectrum of pressure fluctuations, but only with a frequency range near the first resonance. According to the analysis, with increasing elasticity modulus of the coating material E, deformation amplitude decreases as 1/E, and dimensionless velocity of the coating surface decreases as $1/\sqrt{E}$. For sufficiently hard coatings, deformation amplitude becomes smaller than the thickness of viscous sublayer, while surface velocity remains comparable to vertical velocity fluctuations of the flow.

• 동력기계공학회지
• /
• 제5권3호
• /
• pp.48-55
• /
• 2001

In many applications. rubber components undergo dynamic stresses or deformations of fairly large magnitude. Since rubbers are not fully elastic, a part of the mechanical energy is converted into heat due to the hysteresis loss. Heat generation without adequate heat dissipation leads to heat build up. i. e. internal temperature rise. The purpose of this paper is to predict temperature rise caused by the hysteresis loss, in a rubber pad subjected to complex dynamic deformation. In this unsteady thermal analysis, the temperature distributions of track components are displayed in contour shapes and the temperature variations of some important nodes are represented graphically with respect to the running time of the tank.

• 한국항공우주학회지
• /
• 제31권6호
• /
• pp.1-7
• /
• 2003

본 연구에서는 3차원 대칭형 날개의 정상/비정상상대에서의 공기력 특성을 Vortex 패널법을 이용하여 수치적으로 연구했다. 이 프로그램은 날개 표면에 분포된 x, y 방향에 따라 선형적으로 변화는 와(Vortex)를 이용하는 프로그램을 기반으로 하여 3차원 날개 주위의 비압축성 포텐셜 흐름에 적용하였고 박리와 후류의 변형은 고려하지 않았다. NACA Airfoil 자료와 비교한 계산결과는 매우 만족스러운 일치를 보여주었다. 또한 갑작스러운 pitch-up운동과 일정한 각속도로 피칭운동을 하는 비정상 날개에 대해서도 본 방법을 적용하였다. 비정상 상태의 연구에서는 출발와류의 생성과 시간에 따른 위치를 고려함으로서 출발와류가 날개의 공기력 특성에 미치는 영향을 계산하였다. 본 방법은 피칭이나 플래핑, 회전익 해석등의 더 복잡한 경우에도 적용되어질 수 있다.

• 한국정밀공학회:학술대회논문집
• /
• 한국정밀공학회 2002년도 추계학술대회 논문집
• /
• pp.969-974
• /
• 2002

Thermal characteristics according to the cooling methods are studied for the three type spindles with high frequency motor. For the analysis, three dimensional mode]s are built considering heat transfer characteristics such as natural and force convection coefficients. Unsteady-state temperature distributions and thermal deformations according to the cooling conditions are analyzed by using the finite element method.

• 대한조선학회논문집
• /
• 제32권2호
• /
• pp.75-83
• /
• 1995

생산현장의 판굽힘가공 자동화를 위한 기초연구로서 강판의 선상가열 변형을 역학적 측면에서 고찰하고 3차원 비선형 과도 열탄소성 유한요소해석을 통한 수치 시뮬레이션을 시도하였다. 가스토치에 의해 가열되는 평판의 비정상 열전달 문제를 해석하며 온도분포의 시간이력을 계산하였고 이를 바탕으로 평판의 과도 열변형과정을 해석하였으며 그 결과를 상세히 고찰하였다.

• 한국항공우주학회지
• /
• 제45권1호
• /
• pp.1-9
• /
• 2017

본 논문은 초음속 공탄성(aeroelastics) 해석 시간 절약을 위한 준-정상 축약 모델을 제안하고 이를 검증하였다. 유동이 초음속이고 유동의 특성시간이 구조변형의 특성시간에 비해 작을 경우, 유동의 비정상성이 작아 비정상 유동해 대신 정상 유동해를 이용하여 공탄성 해석을 할 수 있다. 크리깅 기법을 적용하여 유동의 축약모델을 구축하였다. 매 시간 축약모델로부터 예측된 표면해가 구조해석의 경계조건으로 사용되었다. 크리킹 기법을 적용한 축약모델을 비정상해석 결과와 비교하여 검증하였다.

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2007년도 춘계학술대회논문집
• /
• pp.275-282
• /
• 2007

In this study, a fluid-structure interaction (FSI) analysis system has been developed in order to evaluate the turbine cascade performance with blade structural deformation effect. Relative movement of the rotor with respect to stator is reflected by modeling independent two computational domains. To consider the deformed position of rotor airfoil, dynamic moving grid method is applied. Reynolds-averaged Navier-Stokes equations with one equation Spalart-Allmaras and two-equation SST $k-{\varepsilon}$ turbulence models are solved to predict unsteady fluid dynamic loads. A fully implicit time marching scheme based on the Newmark direct integration method with high artificial damping is used to compute the fluid-structure interaction problem. Cascade performance evaluations for different elastic axis positions are presented and compared each other. It is importantly shown that the predicted aerodynamic performance considering structural deformation effect of blade can show some deviations compared to the data generally computed from rigid blade configurations and the position of elastic axis also tend to give sensitive effect.