• 한국전산유체공학회지
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• 제5권2호
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• pp.9-19
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• 2000

Transient aerodynamic response of an airfoil to a moving plane-flap is numerically investigated using the two-dimensional Euler equations with conservative Chimera grid method. A body moving relative to a stationary grid is treated by an overset grid bounded by a 'Dynamic Domain Dividing Line' which has an advantage for constructing a well-defined hole-cutting boundary. A conservative Chimera grid method with the dynamic domain-dividing line technique is applied and validated by solving the flowfield around a circular cylinder moving supersonic speed. The unsteady and transient characteristics of the flow solver are also examined by computations of an oscillating airfoil and a ramp pitching airfoil respectively. The transient aerodynamic behavior of an airfoil with a moving plane-flap is analyzed for various flow conditions such as deflecting rate of flap and free stream Mach number.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1999년도 추계 학술대회논문집
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• pp.85-94
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• 1999

Transient aerodynamic response of an airfoil to a moving plane-flap is numerically investigated using two-dimensional Euler equations with conservative Chimera grid method. A body moving relative to a stationary grid is treated by an overset grid bounded by a 'dynamic domain-dividing line' the concept of which is developed in this study. A conservative Chimera grid method with a dynamic domain-dividing line technique is applied and validated by solving the flowfield around circular cylinder moving supersonic speed. The unsteady and transient characteristics of the flow solver is also examined by computations of a oscillating airfoil and a ramp pitching airfoil respectively. The transient aerodynamic behavior of an airfoil with a moving plane-flap is analyzed for various flow conditions such as deflecting rate of flap and free stream Mach number.

• 한국군사과학기술학회지
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• 제10권2호
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• pp.47-52
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• 2007

Missile staging and airframe separation simulation were performed by using a numerical technique for simulating the dynamics of multiple moving bodies. A 6DOF model is fully integrated into the CFD solution procedure to determine the body dynamics. Chimera grid technique offered efficient CFD simulation of multiple moving bodies. Through this simulation the safety of deployed staging and airframe separation mechanism was verified.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1998년도 춘계 학술대회논문집
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• pp.82-89
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• 1998

There are many moving-body problems to be solved, the solution of which necessary for proper design of flight vehicles in aerospace industry. Since a body moves relative to other bodies in the category of these problems, difficulty arises regarding both generation of computational grid around the body in motion and conservation of flow properties in the moving grid system. A few example could be store separation from the aircraft and relative vibration of multiple bodies in the high-speed flow passage. In this paper we report on the progress made in computing moving-body aerodynamics related with sabot separation characteristics. Conservative overlapping grid together with cell-merging-unmerging technique is used to solve the Euler equations for a body in high-speed motion. Carbuncle errors has to be removed before we obtain physically adequate solution. Two-dimensional application is reported here.

• 한국항공운항학회지
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• 제27권4호
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• pp.9-20
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• 2019

A military aircraft generally includes external stores such as fuel tanks or external arming, depending on the purpose of the operation. When a store is dropped from a military aircraft at high subsonic, transonic, or supersonic speeds, the aerodynamic forces and moments acting on the store can be sufficient to send the store back into contact with the aircraft. This can cause damage to the aircraft and endanger the life of the crew. In this study, time accurate computational fluid dynamics (CFD) with dynamic moving grid (moving and deformable mesh, MDM) technique has been used to accurately calculate store trajectories. For the verification of the present numerical approach, a wind tunnel test model for the wing-pylon-finned store configuration has been considered and analyzed. The comparison results for the ejected store trajectories between the present numerical analysis and the wind tunnel test data at the Mach number of 0.95 and 1.2 are presented. It is also importantly shown that the numerical parameter of MDM technique gives significant effect for the calculated store trajectory in the low-supersonic flow such as Mach 1.2.

• Wind and Structures
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• 제5권2_3_4호
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• pp.379-392
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• 2002

Numerical flow computations around an aeroelastic 3D square cylinder immersed in the turbulent boundary layer are shown. Present computational code can be characterized by three numerical aspects which are 1) the method of artificial compressibility is adopted for the incompressible flow computations, 2) the domain decomposition technique is used to get better grid point distributions, and 3) to achieve the conservation law both in time and space when the flow is computed a with moving and transformed grid, the time derivatives of metrics are evaluated using the time-and-space volume. To provide time-dependant inflow boundary conditions satisfying prescribed time-averaged velocity profiles, a convenient way for generating inflow turbulence is proposed. The square cylinder is modeled as a 4-lumped-mass system and it vibrates with two-degree of freedom of heaving motion. Those blocks which surround the cylinder are deformed according to the cylinder's motion. Vigorous oscillations occur as the vortex shedding frequency approaches cylinder's natural frequencies.

• 한국컴퓨터정보학회논문지
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• 제12권2호
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• pp.231-242
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• 2007

패턴 탐사에 관한 기존의 연구들[1,2,3,4,5,6,11,12,13]은 이동 객체의 위치 이력 데이터 집합에 대한 위치 일반화 접근법을 사용하지 않거나 사용해도 특정 공간상의 이동 패턴들 중 단순히 시공간 제약이 없는 빈발 패턴만을 추출하므로, 특정 지점들 간의 최적 이동 경로나 스케줄링 경로와 같은 시공간 제약을 갖는 빈발 패턴 탐사에는 적용하기 어렵다. 또한 패턴 탐사의 수행에 있어 기존의 기법들은 데이터베이스에 대한 반복 접근을 줄이기 위해 메모리 상에 패턴 트리를 생성하여 사용하므로 보다 많은 메모리 공간을 소요하게 된다. 따라서 이러한 기존 탐사 기법들의 문제점들을 해결하기 위한 보다 효율적인 패턴 탐사 기법이 필요한 실정이다. 효율적 탐사 기법을 개발하기 위하여 본 논문에서는 방대한 이동 객체의 이력 데이터 집합에 대한 탐사 수행 시간 및 탐사에 필요한 메모리 공간을 최소화하기 위해서 상세 수준의 데이터들을 의미있는 공간영역 정보로 변환하는 새로운 위치 일반화 방법을 제안한다. 제안된 방법은 패턴 탐사의 전처리 과정에서 $R^*$-Tree와 영역 Grid 해쉬 테이블(AGHT:Area Grid Hash Table)을 기반으로 이동 객체의 위치 속성들을 2차원 공간영역으로 일반화하여 이동 시퀀스를 생성함으로써 효율적인 이동 객체의 공간 이동 패턴 마이닝을 유도할 수 있다.

• 한국전산유체공학회지
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• 제13권3호
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• pp.35-43
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• 2008

A methodology for the simulation of compressible high Reynolds number flow over rigid and moving bodies on a structured Cartesian grid is described in this paper. The approach is based on a modified version of the Brinkman Penalization method. To avoid oscillations in the vicinity of the body and to simulate shcok-containing flows, a Weighted Essentially Non-Oscillatory scheme is used to discretize the spatial flux derivatives. For high Reynolds number viscous flow, two turbulence models of the two-equation Menter's SST URANS model and a two-equation Detached Eddy Simulation are implemented. Some simple flow examples are given to assess the accuracy of the technique. Finally, a moving grid capability is demonstrated.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2007년도 추계 학술대회논문집
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• pp.200-208
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• 2007

A methodology for the simulation of compressible high Reynolds number flow over rigid and moving bodies on a structured Cartesian grid is described in this paper. The approach is based on a modified version of the Brinkman Penalization method. To avoid oscillations in the vicinity of the body and to simulate shcok-containing flows, a Weighted Essentially Non-Oscillatory scheme is used to discretize the spatial flux derivatives. For high Reynolds number viscous flow, two turbulence models of the two-equation Menter's SST URANS model and a two-equation Detached Eddy Simulation are implemented. Some simple flow examples are given to assess the accuracy of the technique. Finally, a moving grid capability is demonstrated.

• 한국정보통신학회논문지
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• 제8권6호
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• pp.1266-1272
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• 2004

위치 기반 서비스는 이동체의 위치에 종속적인 결과를 얻는 위치 기반 질의를 필요로 한다. 이동체의 위치는 연속적으로 변하기 때문에, 이동체의 색인은 변경된 위치 정보를 유지하기 위하여 빈번한 갱신 연산을 수행해야 한다. 기존의 공간 색인들(그리드 파일, R-트리, KDB-트리 등)은 정적 데이터를 검색하는데 효과적인 색인이다. 이들 색인은 연속적으로 위치 데이터가 변경되는 이동체 데이터베이스의 색인으로는 적합하지 않다. 본 논문에서는 삽입/삭제 비용이 적은 동적 해슁 색인을 제안한다. 동적 해슁 색인 구조는 해쉬와 트리를 결합한 동적 해슁 기술을 공간 색인에 적용한 것이다. 실험 결과에서 동적 해슁 색인은 $R^*$-tree와 고정 그리드 보다 성능이 우수하였다.