• 대한기계학회:학술대회논문집
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• 대한기계학회 2004년도 추계학술대회
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• pp.1586-1591
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• 2004

Flow visualization experiments have been performed to investigate the effects of phase lag, reduced frequency qualitatively by examining wake pattern on a dragonfly type wing. The model was built with a scaled-up, flapping wings, composed of paired wings with fore- and hindwing in tandem, that mimicked the wing form of a dragonfly. The present study was conducted by using the smoke-wire technique, and an electronic device was mounted to find the exact positional angle of wing below the tandem wings, which amplitude is ranged from $-16.5^{\circ}$ to $+22.8^{\circ}$. Phase lag applied on the wings is $0^{\circ}$, $90^{\circ}$, $180^{\circ}$ and $270^{\circ}$. The reduced frequency is 0.15, 0.3 and 0.45 to investigate the effect of reduced frequency. It is inferred through observed wake pattern that the phase lag clearly plays an important role in the wake structures and in the flight efficiency as changing the interaction of wings. The reduced frequency also is closely related to wake pattern and determines flight efficiency.

• 한국항공우주학회지
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• 제30권3호
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• pp.8-16
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• 2002

헬리콥터 비행 시뮬레이션을 위한 로터 운동방정식을 implicit formulation 형태로 유도하였다. 좌표계 사이의 상대운동을 고려한 일반화된 벡터 kinematics 를 유도하고 이를 적용하여 브레이드 임의 위치 에서 관성속도 및 관성가속도를 구하였다. 유도된 속도 및 가속도 벡터를 이용하여 플래핑, 리드래그 및 토오크 방정식 등을 implicit form으로 유도하였다. 브레이드 스팬에 따른 공간 적분 방법을 살펴보고, 다양한 힌지형상 및 힌지배열 순서에 관계없이 응용영역을 확장할 수 있음을 밝혔다. DAE(Differential Algebraic Equation) 형태를 갖는 본 연구의 결과식을 이용하여 동특성 계산을 위한 시간적분법을 검토하였다.

• 전기전자학회논문지
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• 제12권2호
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• pp.124-130
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• 2008

벡터 그래픽스는 좌표 정보를 이용하여 이미지를 표현하기 때문에 이미지 퀄리티의 손실 없이 쉽게 확대 축소가 가능하며, 일반적으로 래스터 그래픽스로 표현되는 이미지보다 더 작은 파일 크기를 가진다. 본 논문에서 제안하는 벡터 그래픽 가속기는 개선된 스캔라인 엣지 플래그 방식을 사용하여 엣지의 정렬과정을 수행하지 않고 렌더링을 수행할 수 있도록 설계되었으며 OpenVG 2D 벡터 이미지를 사용하여 검증되었다. 본 논문에서 제안하는 가속기는 Tiger image를 기준으로, 테셀레이션을 수행하는데 12ms, 전체 이미지 렌더링에 208ms의 시간이 소요되며, Tiger image 기준으로 약 초당 5 프레임의 성능을 가진다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2004년도 춘계학술대회논문집
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• pp.337-341
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• 2004

This paper concerns the analytical modeling and dynamic analysis of advanced rotating blade structure implemented by a dual approach based on structural tailoring and viscoelastic materials technology. Whereas structural tailoring uses the directionality properties of advanced composite materials, the passive materials technology exploits the damping capabilities of viscoelastic material(VEM) embedded into the host structure. The structure is modeled as a composite thin-walled beam incorporating a number of nonclassical features such as transverse shear, warping restraint, anisotropy of constituent materials, and warping and rotary inertias. The VEM layer damping treatment is modeled by using the Golla-Mushes-McTavish(GHM) method, which is employed to account for the frequency-dependent characteristic o the VEM. The displayed numerical results provide a comprehensive picture of the synergistic implications of the application of both techniques, namely, the tailoring and damping technology on vibration response of thin-walled beam structure exposed to external time-dependent excitations.

• 한국항공운항학회지
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• 제21권1호
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• pp.45-50
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• 2013

In this study, lumped-vortex element method and thin airfoil theory were used to analyze aerodynamic characteristics of airfoils with relative motion that had camber lines of NACA $44{\times}{\times}$ airfoil in 2-dimensional unsteady incompressible potential flow. Velocity disturbance due to airfoil was calculated by lumped-vortex element model and force distribution on airfoil by unsteady Bernoulli's equation. Variables in relative motion were considered the period p, the amplitude of flapping $A_f$ and pitching $A_p$, and the phase difference between flapping and pitching ${\phi}_p$ and the angle of attack ${\alpha}$. Due to movement of an airfoil, dag was induced in 2-dimensional unsteady incompressible potential flow. The numerical results show that the aerodynamic characteristics of the airfoil with flapping and pitching at the same time are illustrated. Especially the mean lift coefficient became smaller, but drag coefficient became larger.

• 한국항공운항학회지
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• 제14권2호
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• pp.1-8
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• 2006

Unsteady lift measurements were carried out in order to investigate the effects of phase difference and reduced frequency of a dragonfly-type model with two pairs of wing. A load-cell was employed to measure the lift generated by a plunging motion of the dragonfly-type model with the incidence angles of 0$^{circ}$. Experimental conditions are as follows: phase differences between fore- and hind-wings are 0$^{circ}$, 90$^{circ}$, 180$^{circ}$, and 270$^{circ}$, and reduced frequencies are 0.075, 0.15 and 0.225, respectively. The freestream velocity was 143 m/sec and corresponding chord Reynolds number was $3.4{\times}10^3$. The variation of phase-averaged lift coefficients during one cycle of the wing motion is presented. Results show that the total value of the positive lift coefficient during one cycle of the wing motion is the largest at the phase difference of 90$^{circ}$, and that the maximum lift coefficient and lift coefficient per unit of time increases with reduced frequency.

• 한국소음진동공학회논문집
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• 제14권7호
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• pp.639-647
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• 2004

This paper concerns the analytical modeling and dynamic analysis of advanced rotating blade structure implemented by a dual approach based on structural tailoring and viscoelastic material technology. Whereas structural tailoring uses the directionality properties of advanced composite materials, the passive material technology exploits the damping capabilities of viscoelastic material (VEM) embedded into the host structure. The main structure is modeled as a composite thin-walled beam Incorporating a number of nonclassical features such as transverse shear. anisotropy of constituent materials, and rotary inertia etc. The VEM layer damping treatment is modeled by using the Golla-Hughes-McTavish (GHM) method, which is employed to account for the frequency-dependent characteristics of the VEM. The displayed numerical results provide a comprehensive picture of the synergistic implications of both techniques, namely, the tailoring and damping technology on dynamic response of a thin-walled beam structure exposed to external time-dependent excitation.

• 한국항공우주학회지
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• 제34권3호
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• pp.1-5
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• 2006

자연에 존재하는 새나 곤충들은 양력 및 추력을 발생하기 위하여 평균캠버선의 형상을 변화시킨다. 기존의 비정상 박익 이론들은 주로 강체 플랩핑 에어포일에 관하여 유도되어 왔다. 생체형상가변익의 비정상 공력특성을 파악하기 위하여 변형 가능한 에어포일에 대한 확장된 비정상 박익이론이 필요하다. 생체형상가변익의 비정상 공력특성을 계산하기 위해 Theodorsen의 접근방법을 확장하였다. 에어포일의 평균 캠버선은 다항식으로 나타내었다. 형상 가변익에 작용하는 비정상 공력특성을 순환항 및 비순환항으로 나누어 나타내었다. 본 이론은 플래핑운동을 하는 생체형상가변 에어포일의 비정상 공력해석 및 모핑날개의 공탄성 해석에 적용가능하다.

• 한국전산유체공학회지
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• 제14권3호
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• pp.33-48
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• 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
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• 제32권10호
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• pp.118-126
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• 2004

이산와류법(discrete vortex method)을 이용하여 진통하는 평판들로부터 추력발생을 연구하였다. 평판들과 후류들은 이산와류로 나타내었다. 진동하는 평판들 사이의 복잡한 공력상호작용을 정확히 계산하기 위하여 와핵모델(vortex core model)과 와핵첨가법(vortex core addition scheme)을 사용하였다. 단일 평판이 히빙진동을 할 경우 나타나는 후류를 계산하여 기존의 유동가시화 결과와 비교하였다. 피칭진동 시 평판에서 발생하는 후류형상이 평판들의 추진 특성에 미치는 영향을 조사하였다. 3가지 방식(1. 하나의 평판은 고정 다른 평판은 진동, 2. 두개의 평판이 같은 위상으로 진동, 3. 두개의 평판이 반대의 위상으로 진동)으로 진동하는 평판들의 추진특성을 계산하였다. 반대의 위상으로 진통하는 평판이 가장 큰 추진력을 보였다.