• 한국산학기술학회논문지
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• 제21권5호
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• pp.623-629
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• 2020

본 연구는 항공기 기총발사 비행조건에서 Gun Port 주변 공기 유동장을 분석하여 디버터(Diverter) 옵션 형상에 따른 Gun Gas 유동량 및 경로를 확인하고 항공기 성능 및 안전성 영향을 확인하였다. Gun Port Diverter는 기총사격 시 발생하는 열을 효과적으로 낮춰주는 역할을 할 뿐아니라 Gun Gas를 상향방향으로 효율적으로 배출시키는 역할을 수행하며, 그 형상에 따라 Gun Gas 경로가 변경될 수 있다. 후방 Gun Port Diverter의 옵션 형상에 따라 기총 발사 시 Gun Gas의 유량, 경로, 압력을 분석하였다. Gun Port 내부 속도분포와 온도변화를 분석한 결과 후방 Diverter를 지나는 유량은 옵션 형상에 따라 급격이 감소하는 경향을 보이지만, 전방을 지나는 유량은 변화가 적은 비슷한 경향을 보임을 확인하였다. 따라서 기총발사 시 발생하는 Gun Gas는 후방 Gun Port Diverter 옵션 형상과 관계없이 항공기 표면에서 충분한 유동 거리가 확보되며, Diverter 옵션 형상에 따른 Gun Gas 유동의 정체는 Gun Port 내부 온도 상승에 큰 영향을 미침을 확인하였다.

• Smart Structures and Systems
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• 제15권6호
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• pp.1393-1410
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• 2015

An original sensor system based on Fiber Bragg Gratings (FBG) for the strain monitoring of an adaptive wing element is presented in this paper. One of the main aims of the SARISTU project is in fact to measure the shape of a deformable wing for performance optimization. In detail, an Adaptive Trailing Edge (ATE) is monitored chord- and span-wise in order to estimate the deviation between the actual and the desired shape and, then, to allow attaining a prediction of the real aerodynamic behavior with respect to the expected one. The integration of a sensor system is not trivial: it has to fit inside the available room and to comply with the primary issue of the FBG protection. Moreover, dealing with morphing structures, large deformations are expected and a certain modulation is necessary to keep the measured strain inside the permissible measure range. In what follows, the mathematical model of an original FBG-based structural sensor system is presented, designed to evaluate the chord-wise strain of an Adaptive Trailing Edge device. Numerical and experimental results are compared, using a proof-of-concept setup. Further investigations aimed at improving the sensor capabilities, were finally addressed. The elasticity of the sensor structure was exploited to enlarge both the measurement and the linearity range. An optimisation process was then implemented to find out an optimal thickness distribution of the sensor system in order to alleviate the strain level within the referred component.

• 한국환경과학회지
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• 제22권3호
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• pp.347-358
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• 2013

The aerosol number concentration have measured with an aerodynamic particle sizer spectrometer(APS) at Gosan in Jeju Island, which is known as background area in Korea, from March 2010 to February 2011. The obtained results of asian dust events and non-asian dust period have been compared. The results show that the entire averaged aerosol number concentration from APS measurement during asian dust events and non-asian dust period are about 341 particles/$cm^3$ and 240 particles/$cm^3$, respectively. During asian dust events, the number concentration in small size ranges(${\leq}0.4{\mu}m$) are similar to non-asian dust period, however, those in large size ranges(${\geq}0.7{\mu}m$) are very higher than non-asian dust period. The contributions of the size resolved number concentration(23 channel in $0.25{\sim}10.0{\mu}m$) to total number concentration in that range are dramatically decreased with increased particle size. The contributions of smaller size ranges(${\leq}0.4{\mu}m$) during asian dust events are very low compared with non-asian dust period, on the other hand, those of larger size ranges(${\geq}0.4{\mu}m$) are higher than non-asian dust period. The number concentration in each size range are strongly correlated with the concentration in adjacent size range. And the total aerosol number concentration are depended on the number concentration in range of smaller than $0.58{\mu}m$ during non-asian dust period and asian dust events. On the other hand, $PM_{10}$ mass concentration has mainly affected with the number concentration in range of smaller than $1.0{\mu}m$ during non-asian dust period, however, during asian dust events, the mass concentration has mainly affected with the number concentration in range of $0.65{\sim}3.0{\mu}m$.

• 한국공간구조학회논문집
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• 제12권3호
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• pp.47-54
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• 2012

대공간 건축물의 특징 중 경량화 된 지붕 구조 및 재료의 사용으로 인해 지붕면의 손상이나 파괴 등의 피해가 많다. 대규모 경기장의 경우에는 지붕의 구조가 철골 트러스와 인장케이블을 기반으로 테프론이라는 막재료를 사용하여 구조체를 감싸거나 덮는 형태로 많이 설계가 되는데, 특히 이 막재료의 피해가 많으며 심각한 상황이다. 이러한 사례를 통해 대공간 건축물의 지붕에 대한 내풍설계 연구는 아직 미흡한 상태임을 알 수 있다. 본 논문은 쌍곡포물선 대공간구조물의 지붕의 형태에 대한 공기역학적인 특성을 알아보기 위하여 풍압실험과 유체해석을 실시하였다. 실험결과 바람이 불어오는 방향의 지붕 모서리에서 가장 큰 최소피크외압계수가 나타나지만 지붕의 길이방향으로 갈수록 최소피크풍압계수는 감소하고 있었다.

• 한국항공우주학회지
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• 제48권3호
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• pp.187-194
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• 2020

본 연구에서는 고도에 따른 간섭 유동과 공력특성을 파악하고, 측추력 제트에 사용된 기체의 종류에 따라 다화학종 가스제트의 확산을 고려한 유동해석을 수행하였다. 공기제트에 비해서 임의로 가정한 다화학종 가스 제트를 사용하는 경우 충격파의 위치와 제트의 확산 영역이 동체전방으로 이동한다. 이로 인해 표면의 고압영역이 앞으로 나가며 같은 조건에서 보다 높은 피칭 모멘트를 갖는다. 또한 고온효과의 적용에 따라 압력분포 예측에 차이를 보였다. 그리고 저고도의 측추력제트 유동 구조와 비교했을 때 중고도 유동조건에서 주변 대기의 낮은 밀도로 측추력 제트의 두께가 더 크며, 넓은 영역에 걸쳐 확산된다.

• 대한기계학회논문집B
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• 제26권4호
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• pp.604-613
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• 2002

Generation characteristics of electrospray droplets for highly viscous liquid have been investigated by measuring size distributions of droplets emitted from the Taylor cone using glycerol solutions with various conductivities. Because of very small volatility of glycerol, droplet sizes can be measured by an aerodynamic size spectrometer (TSI Aerosizer DSP) with negligible evaporation of droplets. For highly conducting and viscous liquid, the sizes of the droplets electrosprayed from the Taylor cone are found to be relatively insensitive to applied voltages and the electrosprays assisted by the corona discharge call produce monodisperse droplets as long as the corona intensity is not too high. Near the minimum flow rate where a liquid cone is stable, the spray tends to consist of a one -peak monodisperse distribution of drop lets. However, at high flow rates, the spray bifurcates into bimodal distributions, which are consistent with the result of the previous study for less viscous liquids than our liquids. For liquid flow rates (Q) below 1 nl/s, the measured droplet diameters by the aerosizer are in the range of 0.30 to 1.2 ${\mu}{\textrm}{m}$ for the glycerol solutions. The diameters of monodisperse droplets scale approximately with $r^*=Q_$\tau$(Q$\tau$){^1/3}$ where $r^*$ is a characteristic length and $\tau$is the electrical relaxation time of the fluid. However, when compared with several represe ntative scaling laws, the droplet diameters are two to six factors greater than those predicted by the scaling laws. This may be closely related to the combined effect of the much higher viscosity and the electrical charge on the jet breakup of glycerol so solution.

• Wind and Structures
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• 제19권5호
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• pp.481-503
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• 2014

A new theoretical model on rain-wind induced vibration (RWIV) of a continuous stay cable is developed in this paper. Different from the existing theoretical analyses in which the cable was modeled as a segmental rigid element, the proposed scheme focuses on the in-plane and out-of-plane responses of a continuous stay cable, which is identical with the prototype cable on cable-stayed bridge. In order to simplify the complexities, the motion law of the rivulet on the cable surface is assumed as a sinusoidal way according to some results obtained from wind tunnel tests. Quasi-steady theory is utilized to determine the aerodynamic forces on the cable. Equations of motion of the cable are derived in a Cartesian Coordinate System and solved by using finite difference method to obtain the in-plane and out-of-plane responses of the cable. The results show that limited cable amplitudes are achieved within a limited range of wind velocity, which is a unique characteristic of RWIV of stay cable. It appears that the in-plane cable amplitude is much larger than the out-of-plane cable amplitude. Rivulet frequency, rivulet distribution along cable axis, and mean wind velocity profile, all have significant effects on the RWIV responses of the prototype stay cable. The effects of damping ratio on RWIVs of stay cables are carefully investigated, which suggests that damping ratio of 1% is needed to well mitigate RWIVs of prototype stay cables.

• 한국항공우주학회지
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• 제40권2호
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• pp.129-138
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• 2012

에너지 균형조건을 고려하여 중형 태양광 추진 고고도 장기체공 무인기의 다분야 통합 최적설계를 수행하였다. 무인기의 공력 모델로 Vortex Lattice Method (VLM)를 사용하였으며 Cruz가 제안한 중량분석 모델로서 비행체 중량을 추정하였다. 비행체의 세로 정안정성 확보를 위하여 꼬리날개의 부피비를 고정하고 정안정성을 확보할 수 있도록 꼬리날개의 위치를 결정하였다. 태양전지, 축전지, 비행 고도 등 사용가능한 에너지와, 비행체의 필요에너지를 비교하여 24시간 지속비행 가능성을 결정하였다. 태양 입사 에너지는 북위 $36^{\circ}$의 여름을 기준으로 하였으며, 주간비행 중 태양에너지를 이용한 상승비행으로 확보한 위치에너지를 이용하여 야간 비행에 필요한 에너지를 보충하였다. 이를 바탕으로, 무인기의 주요 치수, 중량 분포 최적 설계와 장기체공을 실현할 수 있는 비행전략을 제시하였다.

• Wind and Structures
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• 제31권3호
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• pp.229-240
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• 2020

In the present work, the main features of primary vortices and the vorticity concentrations downstream of vortex bursting in crossflow plane of a delta wing with a sweep angle of Λ=70° were investigated under the variation of the sideslip angles, β. For the pre-review of flow structures, dye visualization was conducted. In connection with a qualitative observation, a quantitative flow analysis was performed by employing Particle Image Velocimetry (PIV). The sideslip angles, β were varied with four different angles, such as 0°, 4°, 12°, and 20° while angles of attack, α were altered between 25° and 35°. This study mainly focused on the instantaneous flow features sequentially located at different crossflow planes such as x/C=0.6, 0.8 and 1.0. As a summary, time-averaged and instantaneous non-uniformity of turbulent flow structures are altered considerably resulting in non-homogeneous delta wing surface loading as a function of the sideslip angle. The vortex bursting location on the windward side of the delta wing advances towards the leading-edge point of the delta wing. The trajectory of the primary vortex on the leeward side slides towards sideways along the span of the delta wing. Besides, the uniformity of the lift coefficient, C_L over the delta wing plane was severely affected due to unbalanced distribution of buffet loading over the same plane caused by the variation of the sideslip angle, β. Consequently, dissimilarities of the leading-edge vortices result in deterioration of the mean value of the lift coefficient, C_L.

• 한국항공우주학회지
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• 제44권6호
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• pp.520-529
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• 2016

본 연구의 목적은 중고도-장기체공 무인기의 성능을 역설계를 통해 분석하는 것이며, 역설계를 위한 모델로 RQ-1 Predator를 선정하였다. CATIA 프로그램을 사용하여 RQ-1 Predator의 외형에 대한 형상과 중량 분포를 생성하였다. RQ-1 Predator의 공력특성은 주로 와류격자법과 경험식을 조합하여 수행하였으며, 추진 성능은 Howe의 경험식을 통해 수행되었다. 상승률, 실용상승한도, 항속 거리, 그리고 체공 시간에 대한 역설계를 수행하였으며, 역설계 결과가 참고문헌과 잘 일치함을 확인하였다.