• 설비공학논문집
• /
• 제17권1호
• /
• pp.33-38
• /
• 2005

This study has been conducted to investigate flow characteristics of a micropump with piezoelectric materials. In this study, the change of flow rates has been investigated for different positions of the inlet and outlet and for different distances between them. The FSI(Fluid Structure Interaction) method has been employed for numerical analysis of the piezoelectric diffuser/nozzle based micropump. It has been found that time averaged flow rate is greater in the case that distance between the inlet and outlet is longer. For the cases where the positions of the inlet are different with the position of the fixed outlet at the center, the flow rate is increased as the inlet is located farther from the center. This study may supply fundamental understandings for the design and analysis of the prototypes of piezoelectric micropumps.

• 대한조선학회논문집
• /
• 제48권6호
• /
• pp.552-559
• /
• 2011

An interest in Arbitrary Lagrangian Eulerian (ALE) finite element methods has been increased due to more accurate responses in Fluid-Structure Interaction(FSI) problems. The multi-material ALE approach was applied to the prediction of the acceleration response of free-fall lifeboat, and its responses were compared to those of the single-material ALE one. It could be found that even though there was no big difference in the simulation responses of two methods, the single-material and multi-material ALE ones, the latter multi-material ALE method showed a little bit more close response to those of experimental results compared to the former single-material ALE one, especially in the x- and z-direction acceleration responses. Through this study, it could be found that several parameters in the ALE algorithms have to be examined more carefully for a good structural safety assessment of FSI problems.

• 한국항공운항학회지
• /
• 제17권2호
• /
• pp.8-17
• /
• 2009

In this study, flutter analyses for supercritical airfoil have been conducted in transonic region. Advanced computational analysis system based on computational fluid dynamics (CFD) and computational structural dynamics (CSD) has been developed in order to investigate detailed static and dynamic responses of supercritical airfoil. Reynolds-averaged Navier-Stokes equations with Spalart-Allmaras (S-A) and SST ${\kappa}-{\omega}$ turbulence models are solved for unsteady flow problems. A fully implicit time marching scheme based on the Newmark direct integration method is used for computing the coupled aeroelastic governing equations of cascades for fluid-structure interaction (FSI) problems. Also, flow-induced vibration (FIV) analyses for various supercritical airfoil models have been conducted. Detailed flutter responses for supercritical are presented to show the physical performance and vibration characteristics in various angle of attack.

• International Journal of Aerospace System Engineering
• /
• 제8권1호
• /
• pp.1-13
• /
• 2021

Contra-rotating fan is comprised of two rotors which are rotating in the opposite direction. The fan stages are named rotor-1 and rotor-2. Benefits from the use of contra rotation are in terms of better efficiency and improved thrust to weight ratio. Failure of contra-rotating fan stage blade in-service results in safety risks, repair costs, and revenue losses. This paper focuses on the vibration analysis and one way fluid-structure interaction of high aspect ratio, low speed contrarotating fan rotors. Modal analysis and modal pre-stress analysis of contra-rotating fan rotors were carried out to calculate the natural frequencies, One way fluid-structure interaction (FSI) was carried out where the computational analysis of the blades was performed using ANSYS CFX. The boundary conditions for CFD analysis were considered from the actual experimental velocity flow field at the inlet and pressure outlet. Based on the results obtained from the CFD analysis, the structural analysis such as deformation and Von-Misses stresses was carried out by using the finite element method (FEM) with ANSYS. The results provide necessary guidelines for the safe running of the contra-rotating fan. The analysis also will be helpful to understand the change of flow behavior due to a rotor deformation.

• 한국항공우주학회지
• /
• 제40권11호
• /
• pp.957-962
• /
• 2012

비행체 구조는 공기력에 의해 변형이 발생하고 이 구조의 변형은 다시 공기력의 변화를 유발하므로 비행체 구조 시스템의 고정밀 설계를 위해서는 공력/구조 연계 해석이 필요하다. 그러나 발생하는 변형이 비선형 구조 해석을 요구할 정도로 큰 경우, 선형 시스템에서와 같이 공력 해석과 구조 해석을 순차적으로 반복하는 연계 해석 기법은 바람직하지 않다. 구조적 변형에 따라 변하는 공기력을 충분히 고려하지 못하며, 소요 시간 또한 크기 때문이다. 본 연구는 공력장 내부의 비선형 구조의 거동을 보다 효율적으로 예측할 수 있는 공력/구조 연계 해석 기법을 다룬다. 즉, 비선형 구조 해석 단계 도중에 주기적으로 공력 해석을 통한 외력 업데이트를 수행하는 알고리즘을 제안한다. 또한 고세장비의 유연날개를 가지는 글로벌 호크 모델을 사용하여 여러 가지 기법의 비선형 공력/구조 연계 해석의 결과를 비교하였다.

• Interaction and multiscale mechanics
• /
• 제5권3호
• /
• pp.287-318
• /
• 2012

We apply a partitioned-solution (iterative-staggered) coupling method based on a fixed Eulerian mesh with the level set function to a large-deformation fluid-structure interaction (FSI) problem where a large-deformable thin structure moves in a high-speed flow field, as an airbag does during deployment. This method combines advanced fluid and structure solvers-specifically, the constrained interpolation profile finite element method (CIP-FEM) for fluid Eulerian mesh and large-deformable structural elements for Lagrangian structural mesh. We express the large-deformable interface as a zero isosurface by the level set function, and introduce virtual nodes with level sets and structural normal velocities to generate the level set function according to the large-deformable interfacial geometry and enforce the kinematic condition at the interface. The virtual nodes are located in the direction normal to the structural mesh. It is confirmed that application of the method to unfolded airbag deployment simulation shows the adequacy of the method.

• 한국전산구조공학회논문집
• /
• 제20권1호
• /
• pp.83-92
• /
• 2007

대형의 유체-구조물 연계시스템(FSI) 해석을 위해 많은 수치기법들이 있지만, 유체의 슬로싱에 의해 발생되는 집중적이고 불규칙한 동수압의 영향 때문에, 신뢰할 수 있는 수치 결과와 수치안정성을 확보하기 위해 매우 조밀한 메쉬를 필요로 한다. 그 결과, 신뢰할 수 있는 장기적인 시간 응답을 구하기 위한 수치해석은 상당히 많은 CPU 시간을 요구한다. 본 논문의 목적은 국부 상세 모델을 이용하여 LNG운반선의 화물창 시스템의 유탄성적 거동을 해석하기 위한 전역-국부 해석기법을 제시하고자 한다. 본 논문에서 제시한 해석기법의 타당성을 증명하고 이 기법을 통해 LNG운반선 화물창 시스템의 국부응답을 효율적으로 예측한 결과를 제시하였다.

• 화약ㆍ발파
• /
• 제38권3호
• /
• pp.15-29
• /
• 2020

본 논문에서는 Hoek-Brown (HB) 파괴기준을 Holmquist-Johnson-Cook (HJC) 콘크리트 재료모델에 접목시킴으로써 LS-DYNA 상에서 암반발파를 모델링할 때 현장암반의 고유한 특성이 잘 반영될 수 있도록 도모하였다. 이것은 많은 지질학적 불연속면을 포함하고 있는 현장암반이 지니고 있는 독특한 특징을 강조하기 위함이다. 두 모델의 접목은 HB 파괴기준으로 HJC 재료모델의 정적 강도 부분을 교체함으로써 이루어지며, 교체과정은 통계학적 곡선적합 기법에 의해 수행된다. 본 논문에서는 접목의 과정이 상세하게 소개되며, 획득된 HJC 재료모델의 사용에 대한 실례도 제시된다. 제시된 수치계산은 현장의 석회암 암반의 단일공 발파에 대한 평면변형률 모델링으로서 LS-DYNA가 제공하는 유체-구조물 상호작용(FSI) 기법과 다중재료 라그랑주-오일러(MMALE) 정식화 기법을 조합하여 수행된다.

• 융합정보논문지
• /
• 제10권2호
• /
• pp.82-88
• /
• 2020

본 연구는 화공용 열교환기에서 법랑코팅 적용을 위한 고온의 소성 공정조건 최적화에 대한 기초자료를 얻고자 하는데 그 목적이 있다. Shell & Tube 형태인 열교환기에 법랑코팅 적용을 위해 소성온도를 순차적으로 높이는 방안에 대해 검토하였다. 소성로 내부에서 열교환기의 온도분포에 대해 CFD 상용 프로그램으로 수치계산하여 구한 온도를 하중조건으로 열응력 해석을 수행하는 연성 해석(FSI) 방식을 이용하여 열교환기의 구조 안전성에 미치는 영향을 확인하였다. 수치해석 및 실험결과 상온의 열교환기를 바로 860℃도의 소성로에 넣으면 열교환기의 국부적 온도차로 인한 구조 안전성에 문제가 발생하므로 온도차를 줄이기 위한 예열 과정이 필요하다. 소성공정 단계가 적은 Case2와 같이 1단계 예열온도 445℃, 2단계 소성온도 860℃가 가장 적합한 것으로 판단된다.

• International Journal of Naval Architecture and Ocean Engineering
• /
• 제5권1호
• /
• pp.116-131
• /
• 2013

The resistance performance of an icebreaking cargo vessel in pack ice conditions was investigated numerically and experimentally using a recently developed finite element (FE) model and model tests. A comparison between numerical analysis and experimental results with synthetic ice in a standard towing tank was carried out. The comparison extended to results with refrigerated ice to examine the feasibility of using synthetic ice. Two experiments using two different ice materials gave a reasonable agreement. Ship-ice interaction loads are numerically calculated based on the fluid structure interaction (FSI) method using the commercial FE package LS-DYNA. Test results from model testing with synthetic ice at the Pusan National University towing tank, and with refrigerated ice at the National Research Council's (NRC) ice tank, are used to validate and benchmark the numerical simulations. The designed ice-going cargo vessel is used as a target ship for three concentrations (90%, 80%, and 60%) of pack ice conditions. Ice was modeled as a rigid body but the ice density was the same as that in the experiments. The numerical challenge is to evaluate hydrodynamic loads on the ship's hull; this is difficult because LS-DYNA is an explicit FE solver and the FSI value is calculated using a penalty method. Comparisons between numerical and experimental results are shown, and our main conclusions are given.