• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2005년도 제25회 추계학술대회논문집
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• pp.86-89
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• 2005

2단식 경가스총으로 부터 발사된 발사체의 공기역학적 특성을 연구하기 위해 이동 경계 수치계산법을 축대칭 비정상 압축성 오일러 방정식에 적용하였다. 본 연구로 얻어진 결과는 초음속으로 발사된 발사체로 인한 충격파와 폭발파사이 간섭현상, 와류와 barrel 충격파사이의 간섭현상, 정상 부족팽창 제트을 관찰할 수 있었으며, 발사체 질량 변화에 따른 발사체의 속도, 가속도, 항력 선도를 예측하였다.

• 한국해양공학회지
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• 제16권6호
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• pp.7-17
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• 2002

Recently, artificial rocks, instead of buoys, have been placed on the submerged breakwater to indicate its location. The accurate estimation of wave forces on these rocks is deemed necessary for their stability design. Characteristics of the wave force, however, are expected . to be very complicated because of the occurrence of breaking or post-breaking waves. In this regard, wave forces exerted on an artificial rock have been investigated in this paper. The maximum wave force has been found to strongly dependent on the location and shape of the artificial rock that is placed on the submerged breakwater. The plunging breaker occurs near the loading cram edge of a submerged breakwater, which cause impulsive breaking wave force on the rock. Using the Morison equation, with the velocity and acceleration at the front face of the artificial rock and varying water surface level, it is possible to estimate wave forces, even impulsive breaking wave forces, that are acting on the rock installed on a submerged breakwater. The vertical wave force is also found to depend, significantly, on the buoyant force.

• Journal of Astronomy and Space Sciences
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• 제32권3호
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• pp.189-200
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• 2015

In this study, we present the results of orbit determination (OD) using satellite laser ranging (SLR) data for the Science and Technology Satellite (STSAT)-2C by a short-arc analysis. For SLR data processing, the NASA/GSFC GEODYN II software with one year (2013/04 - 2014/04) of normal point observations is used. As there is only an extremely small quantity of SLR observations of STSAT-2C and they are sparsely distribution, the selection of the arc length and the estimation intervals for the atmospheric drag coefficients and the empirical acceleration parameters was made on an arc-to-arc basis. For orbit quality assessment, the post-fit residuals of each short-arc and orbit overlaps of arcs are investigated. The OD results show that the weighted root mean square post-fit residuals of short-arcs are less than 1 cm, and the average 1-day orbit overlaps are superior to 50/600/900 m for the radial/cross-track/along-track components. These results demonstrate that OD for STSAT-2C was successfully achieved with cm-level range precision. However its orbit quality did not reach the same level due to the availability of few and sparse measurement conditions. From a mission analysis viewpoint, obtaining the results of OD for STSAT-2C is significant for generating enhanced orbit predictions for more frequent tracking.

• 한국기계가공학회지
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• 제5권4호
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• pp.13-20
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• 2006

The inherent problem of a Darrieus wind turbine is its inability to self-start. Usually, a motor is used to provide angular acceleration until lift forces are produced in the airfoil blades or up until the turbine can already sustain its speed on its own. This paper describes a method of improving the self-starting of an H-type Darrieus vertical axis wind turbine (VAWT) by incorporating a helical Savonius turbine thus utilizing a drag-lift combination. The effect of each turbine in the combination relative to each other is investigated by testing a prototype windmill consisting of three NACA 0015 airfoil blades combined with a Savonius rotor with a helix angle of 180 degrees and whose swept area equals 30% of the entire turbine.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.546-549
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• 2008

Institute of Space and Astronautical Science of Japan Aerospace Exploration Agency(ISAS/JAXA) successfully developed and operated the microwave discharge ion engines onboard Hayabusa asteroid explorer. The ${\mu}10$ ion engines feature the cathode-less plasma generation in both the ion generators and neutralizers with the results of long life and high reliability in space. Based on the space achievements of ${\mu}10$ ion engines with 8mN thrust, 3,000sec Isp and 350W consumption power, several programs are currently under developments: ${\mu}20$, ${\mu}10$HIsp and ${\mu}1$. The first is a 20-cm diameter microwave discharge ion engine, aiming to achieve 30mN/kW in the thrustto-power ratio for the asteroid sample return mission larger than Hayabusa. The second is a high Isp version of ${\mu}10$, and exhausts the plasma beam over 10,000sec Isp using 15kV acceleration voltage for deep space missions to such as Jupiter and Mercury. The third is ${\mu}1$ to be adapted to small satellites for drag-free.

• Wind and Structures
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• 제35권2호
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• pp.109-120
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• 2022

The force coefficients of rotating plates in the acceleration stage will vary with rotation rate from 0 to stable rotation rate w₀, which are important for quasi-steady theory of plate-like windborne debris to simulate the trajectory. In this paper, a wind tunnel experiment is carried out to study the effects of geometry and the Reynolds number on the variations of mean force coefficients of rotating plates. The rotational lift coefficients are sensitive to both geometry effect and Reynolds number effect, while the rotational drag and moment coefficients are only sensitive to geometry effect. In addition, new empirical formulas for the rotational lift coefficient and moment coefficients are proposed. Its accuracy is verified by comparing the predicted results with existing test data. Based on the experimental data of rotating plates, a new rotational force model for quasi-steady theory, which can be applied to a wider scope, is proposed to calculate the trajectory of plate-like windborne debris. The results show that the new model provides a better match with the tested trajectories than previous quasi-steady theories.

• Journal of Astronomy and Space Sciences
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• 제26권2호
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• pp.229-236
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• 2009

다목적실용위성-5호는 2010년 발사를 목표로 고도 550km의 저궤도에 위치하게 될 것이다. 다목적실용위성-5호의 임무인 고정밀 SAR(Synthetic Aperture Radar) 영상을 처리하기 위해서는 정확한 위성의 위치(20cm) 와 속도(0.03cm/s)가 결정되어야 한다. 이러한 요구 조건은 한국 전자통신연구원에서 개발한 ETRI GNSS Precise Orbit Determination(EGPOD) 소프트웨어로 검증하였다. 0.1Hz 수신 주기의 SAC-C 위성 반송파위상 데이터로 정밀궤도결정을 수행하였다. 이중 주파수 GPS 데이터를 사용하여 수신 선호의 전리층 오차를 대부분 제거하고 이중 차분된 데이터를 생성함으로써 GPS 위성과 수신기의 공통된 시계 오차를 없앴다. 동역학 모델 접근 방법을 이용하였고, Batch Least Square Estimator(BLSE) 필터로 각 데이터 아크(arc) 에 해당하는 위성의 위치와 속도, 대기저항 계수, 태양풍 계수를 추정하였다. 또한 정밀한 동역학 모델을 위하여 모델 되지 않은 부정확한 가속도 항을 보충하는 경험 가속도를 추가하였다. 경험 가속도는 위성의 공전 주기(revolution) 당 한번씩 시선방향(radial), 진행방향(along-track), 수직방향(cross-track)으로 추정하고, 수직방향의 상수 항에 대해서는 해당 데이터 아크에 관하여 부가적으로 추정하였다. 정밀궤도결정 결과 검증을 위하여 EGPOD 소프트웨어에서 얻어진 결과와 JPL에서 제공하는 정밀궤도력(Precise Orbit Ephemeris)을 비교하였다.

• 대한기계학회논문집B
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• 제34권4호
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• pp.355-364
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• 2010

주위 매질의 움직임에 반응하는 섬유상 감지모는 대부분의 생물체에 존재하여 침입자를 감지하는 역할을 한다. 이 기능을 모방한 인공 감지모의 가능한 작동영역 및 응답특성을 파악하기 위하여 인공유동센서의 수학 모델에 대한 매개변수 해석을 수행하고, 각 변수들의 영향을 고찰하였다. 진동성분을 갖는 복합 공기 유동장에서 감지모의 길이 및 직경이 기계적인 감도와 주파수 응답을 결정하는 주요 인자인 것으로 나타났다. 감지모의 길이에 따라 각속도, 각속도, 각가속도를 감지할 수 있는 주파수 영역이 달라질 수 있는 것으로 나타났다. 또한 항력 및 가상 질량에 의한 토크가 매우 작지만 감지모의 움직임에 매우 큰 영향을 나타냈다. 감지모의 길이 및 직경이 증가함에 따라 공진 주파수는 감소하는 것으로 나타났다.

• 한국항공우주학회지
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• 제38권7호
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• pp.637-646
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• 2010

포텐셜 기저 패널법과 시간전진법을 통합한 시간영역 패널법을 이용하여 융합익기 형상 초소형 무인기 FM07에 대한 정상/비정상 공력해석을 수행하였다. 융합익기 형상 무인기인 FM07의 공력해석에는 초기 설계형상(Case I)과 가로세로비를 증가시키고 무게중심을 후방으로 이동시킨 개선형상(Case II)이 사용되었다. 정상 공력해석을 통해 FM07 무인기의 개선형상이 초기형상에 비하여 보다 큰 양항비와 높은 피칭 안정성을 나타냄을 확인하였다. FM07의 비정상 급가속(발사체 이륙단계)을 나타낸 공력해석에서는 초기 급격한 증가를 보이는 공력계수들이 수초 후에 안정화되어 정상상태에 근사한 값을 나타내었다. FM07의 순항시 발생할 수 있는 피치진동운동에 대한 해석을 수행하여 진동에 따른 공력계수의 이력 현상을 확인하였으며, 개선형상이 보다 큰 민감도를 갖는 것을 확인하였다.

• 한국항해학회지
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• 제23권2호
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• pp.29-42
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• 1999

An accurate method of estimating ship maneuverability needs to be developed to evaluate precisely and improve the maneuverability of ships according to the water depth. In order to estimate maneuverability by a mathematical model. The hydrodynamic forces acting on a ship hull and the flow field around the ship in maneuvering motion need to be estimated. The ship speed new the berth is very low and the fluid flow around a ship hull is unsteady. So, the transient fluid motion should be considered to estimate the drag force acting on the ship hull. In the low speed and short time lateral motion, the vorticity is created by the body and grow up in the acceleration stage and the velocity induced by the vorticity affect to the body in deceleration stage. For this kind of problem, CFD is considered as a goof tool to understand the phenomena. In this paper, the 2D CFD code is used for basic consideration of the phenomena to solve the flow in the cross section of the ship considering the ship is slender and the water depth is large enough. The flow fields Added and hydrodynamic forces for the some prescribed motions are computed and compared with the preliminary experiment results. The comparison of the force with measurement is shown a fairly good agreement in tendency. The 3D Potential Calculation based on the Hess & Smith Theory is employed to predict the surge, sway added mass and yaw added moment of inertia of hydrodynamic coefficients for M/V ESSO OSAKA according to the water depth. The results are also compared with experimental data. Finally, the sway added mass of hydrodynamic coefficients for T/S HANNARA is suggested in each water depth.