• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 1999년도 제13회 학술강연논문집
• /
• pp.33-33
• /
• 1999

The Coanda effect is the tendency for a fluid jet to atach itself to an adjacent surface and follow its contour without causing an appreciable flow separation. The jet is pulled onto the surface by the low pressure region which develops as entrainment pumps fluid from the region between the jet and the surface. Then the jet is held to the wall surface by the resulting radial pressure gradient which balance the inertial resistance of the jet to turning. The jet may attach to the surface and may be deflected through more than 180 dog, when the radius of the Coanda surface is sufficiently large compared to the height of the exhaust nozzle. However, if the radius of curvature is small, the jet turns through a smaller angle, or may not attach to the surface at all. In general, the limitations in size and weight of a device will limit the radius of the deflection surface. Thus much effort has been paid to improve the jet deflection in a variety of engineering fields. The Coanda effect has long been applied to improve aerodynamic characteristics, such as the drag/lift ratio of flight body, the engine exhaust plume thrust vectoring, and the aerofoil/wing circulation control. During the energy crisis of the seventies, the Coanda jet was applied to reduce vehicle drag and led to drag reductions of as much as about 30% for a trailer configuration. Recently a variety of industrial applications are exploiting another characteristics of the Coanda jets, mainly the enhanced turbulence levels and entrainment compared with conventional jet flows. Various industrial burners and combustors are based upon this principle. If the curvature of the Coanda surface is too great or the operating pressure too high, the jet flow will break away completely from the surface. This could have catastrophic consequences for a burner or combustor. Detailed understanding of the Coanda jet flow is essential to refine the design to maximize the enhanced entrainment in these applications.

• 한국공작기계학회:학술대회논문집
• /
• 한국공작기계학회 2005년도 춘계학술대회 논문집
• /
• pp.216-227
• /
• 2005

The head penetrations for control rod drive mechanism and instrumentation systems are installed at the reactor pressure vessel head of PWRs. Primary coolant water and the operating conditions of PWR plants can cause cracking of these nickel-based alloy through a process called primary water stress corrosion cracking (PWSCC). Inspection of the head penetrations to ensure the integrity of the head penetrations has been interested since reactor coolant leakages were found at U. S. reactors in 2000 and 2001. The complex geometry of the head penetrations and the very low echo amplitude from the fine, multiple flaws due to the nature of the see made it difficult to detect and size the flaws using conventional pulse-echo UT methods. Time-of-flight-diffraction technique, which utilizes the time difference between the flaw tips while pulse-echo does the flaw response amplitude from the flaw, has been selected for this inspection for it's best performance of the detection and sizing of the head penetration see flaws. This study defines the limits of the detectable and accurately sizable minimum flaw size which can be detected by the General TOFD and the Delta TOFD techniques for circumferentially and axially oriented flaws respectively. These results assures the reliability of the inspection techniques to detect and accurately size for various kind of flaws, and will also be utilized for the future development and qualifications of the TOFD techniques to enhance the detecting sensitivity and sizing accuracy of the flaws of the reactor head penetrations in nuclear power plants.

• 폴리머
• /
• 제33권6호
• /
• pp.620-624
• /
• 2009

의료용 금속 임플란트는 우수한 기계적 강도를 바탕으로 결손된 신체 부위의 보강, 대치, 회복을 위해 임상적으로 사용되고 있지만, 낮은 생체적합성 및 독성 때문에 염증 및 후기 혈전증, 재협착의 문제점을 가지고 있다. 이런 단점을 보안하기 위한 다양한 표면처리 기술 중, 본 연구에서는 금속표면에 생분해성 고분자인 poly (lactic-co-glycolic acid) (PLGA)를 이용하여 전기분사 코팅(electrospray coating) 기술을 검토하였다. 전기분사와 용액 인자들의 기초적인 조사를 바탕으로, 코팅 필름의 표면형상은 방울이 날아가는 거리, 용매의 비등점, 방울의 크기에 밀접한 관련이 있다. 고분자 필름의 두께는 분사량에 선형적으로 비례를 하였다. 이 결과는 전기분사된 고분자 방울이 계속적으로 고분자 필름 위에 적층되는 것을 보여준다. 따라서, 전기분사 코팅기술은 스텐트와 같은 의료용 금속 임플란트에 있어서 표면 형상 조절, 나노/마이크로 두께의 단/다중층의 고분자 필름을 제조하는데 적용될 수 있다.

• 한국측량학회지
• /
• 제22권3호
• /
• pp.277-284
• /
• 2004

본 연구는 접경지역에 인접한 지역의 특성상 항공사진 촬영이 불가능한 지역 중 파주시에 대하여 1m 고해상도 스테레오 영상을 이용하여 1/5,000 대축척 수치지도 제작에 시험 적용한 연구이다. 위성영상의 정밀기하보정을 위하여 GPS 관측에 의하여 획득된 지상기준점을 이용하였으며, IKONOS 스테레오 영상과 디지털 해석도화기를 이용하여 수치지도를 제작하였다. 제작된 수치지도에 대하여 GPS를 이용한 현지 검사점 측량을 실시한 결과 평면과 수직위치의 RMSE는 각각 $\pm$1.706m와 $\pm$1.231m로 관측되었다. 이 수평과 수직위치 RMSE는 NGIS 수치지도의 정확도를 만족하는 값으로써 본 연구를 통하여 제안된 새로운 방법은 군사적 원인으로 인한 비행금지구역의 대축척 수치지도 제작을 위한 좋은 기회라고 할 수 있다.

• 한국측량학회지
• /
• 제27권2호
• /
• pp.261-271
• /
• 2009

최근 도시의 3차원 공간정보에 대한 필요성이 증가함에 따라 연직사진과 경사사진을 동시에 촬영하는 항공용 다각카메라에 대한 관심이 높아지고 있다. 기존의 지형공간정보는 주로 연직사진에 의존하지만 다각 카메라는 연직사진 뿐 아니라 사방에서 촬영된 경사사진도 함께 이용하므로 사용자가 대상물을 쉽게 판독할 수 있게 한다. 본 연구에서는 카메라시스템, GPS/INS, 촬영안내시스템, 제어시스템으로 구성된 다각사진촬영시스템 프로토타입을 개발하고, 실제 항공촬영에 통해 장비개발 시 고려해야 할 카메라 설치 각도, 동시촬영, 촬영시간지연, 저장 등에 대해 실험하였다.

• 한국항공운항학회지
• /
• 제13권3호
• /
• pp.73-84
• /
• 2005

Hanseo University's Tae-an Airfield was opened in July, 2005 for aeronautical education such as aircraft flight, air traffic control, avionics, etc., and will play an important part as a base for local economic and industrial developments. On the contrary, the aircraft noise from the airfield will give an impact against the vicinity of the airfield and become a big issue which the airfield authority has to solve. The aim of this study is to analyse the aircraft noise contour in vicinity of the airfield and to make understand the people around the airfield how much the aircraft noise will have an effect on. For the prediction of the aircraft noise in the local area, this study showed the method to assess the aircraft noise in the developed countries for aviation, and the result to compute WECPNL by INM 6.1 after encoding the various data including environmental input data, tract, and profile. The major results of the study can be summarized as follows ; While the area with influence contour of noise from 75 to 80 WECPNL is 0.555$km^2$, the area from 80 to 85 is 0.343$km^2$, and the area with influence contour of noise over 85 WECPNL is 0.163$km^2$. In addition, there are 4 houses in the contour over 85 WECPNL and the inhabitants(10 people) in this area will have effect from the noise. Therefore Tae-an airfeild authority is preparing the noise-prevention method or noise abatement program. Finally, according to the noise contour, it is one of the best way of decreasing the effect of aircraft noise that 33 runway is assigned as calm-wind runway because there is no resident in the area around 15 threshold.

• 대한전기학회:학술대회논문집
• /
• 대한전기학회 2006년도 제37회 하계학술대회 논문집 C
• /
• pp.1629-1630
• /
• 2006

This paper describes a micro total analysis system ($\mu$ TAS) for detecting and digesting the target protein which includes a bead based temperature controllable microchip and computer based controllers for temperature and valve actuation. We firstly combined the temperature control function with a bead based microchip and realized the on-chip sequential reactions using two kinds of beads. The PEG-grafted bead, on which RNA aptamer was immobilized, was used for capturing and releasing the target protein. The target protein can be chosen by the type of RNA aptamer. In this paper, we used the RNA aptamer of HCV replicase. The trypsin coated bead was used for digesting the released protein prior to the matrix assisted laser desorption ionization time of flight mass spectrometer (MALDI TOF MS). Heat is applied for release of the captured protein binding on the bead, thermal denaturation and trypsin digestion. PDMS microchannel and PDMS micro pneumatic valves were also combined for the small volume liquid handling. The entire procedures for the detection and the digestion of the target protein were successfully carried out on a microchip without any other chemical treatment or off-chip handling using $20\;{\mu}l$ protein mixture within 20 min. We could acquire six matched peaks (7% sequence coverage) of HCV replicase.

• 한국항공우주학회지
• /
• 제31권1호
• /
• pp.113-119
• /
• 2003

위성의 추진제량은 위성의 임무운용기간을 결정하는 주요 변수들 중의 하나이며, 현재 운용중인 위성의 추진제 잔량을 정확하게 예측하는 일은 향후 위성의 운용계획을 수립함에 있어 매우 중요하다. 일반적으로 인공위성의 추진제 소모량을 계측하기 위해서는 PVT 방식이나 회계식 방법이 이용되어지며, 본 논문에서는 다목적실용위성 1호의 실제 원격 측정 자료에 근거하여 상기의 두 가지 계측법을 비교, 분석하고 각각의 특징들에 대해 고찰하고 있다. 또한 위성의 주된 추력기 작동 모드인 안전모드에서 추력기를 사용하지 않는 과학임무모드로 복귀하는 과정에서 여러 단계의 자세제어모드에 따른 추진제 소모율에 대해 상세히 검토하였다. 계산결과 지구찾기모드에서 추진제 소모율이 최고치를 보였다.

• Journal of Astronomy and Space Sciences
• /
• 제30권4호
• /
• pp.335-344
• /
• 2013

TRiplet Ionospheric Observatory-CubeSat for Ion, Neutron, Electron & MAgnetic fields (TRIO-CINEMA) is a CubeSat with 3.14 kg in weight and 3-U ($10{\times}10{\times}30$ cm) in size, jointly developed by Kyung Hee University and UC Berkeley to measure magnetic fields of near Earth space and detect plasma particles. When a satellite is launched into orbit, it encounters ultra-high vacuum and extreme temperature. To verify the operation and survivability of the satellite in such an extreme space environment, experimental tests are conducted on the ground using thermal vacuum chamber. This paper describes the temperature control device and monitoring system suitable for CubeSat test environment using the thermal vacuum chamber of the School of Space Research, Kyung Hee University. To build the chamber, we use a general purpose thermal analysis program and NX 6.0 TMG program. We carry out thermal vacuum tests on the two flight models developed by Kyung Hee University based on the thermal model of the TRIO-CINEMA satellite. It is expected from this experiment that proper operation of the satellite in the space environment will be achieved.

• Journal of Astronomy and Space Sciences
• /
• 제33권4호
• /
• pp.323-333
• /
• 2016

In this study, the uncertainty requirements for orbit, attitude, and burn performance were estimated and analyzed for the execution of the $1^{st}$ lunar orbit insertion (LOI) maneuver of the Korea Pathfinder Lunar Orbiter (KPLO) mission. During the early design phase of the system, associate analysis is an essential design factor as the $1^{st}$ LOI maneuver is the largest burn that utilizes the onboard propulsion system; the success of the lunar capture is directly affected by the performance achieved. For the analysis, the spacecraft is assumed to have already approached the periselene with a hyperbolic arrival trajectory around the moon. In addition, diverse arrival conditions and mission constraints were considered, such as varying periselene approach velocity, altitude, and orbital period of the capture orbit after execution of the $1^{st}$ LOI maneuver. The current analysis assumed an impulsive LOI maneuver, and two-body equations of motion were adapted to simplify the problem for a preliminary analysis. Monte Carlo simulations were performed for the statistical analysis to analyze diverse uncertainties that might arise at the moment when the maneuver is executed. As a result, three major requirements were analyzed and estimated for the early design phase. First, the minimum requirements were estimated for the burn performance to be captured around the moon. Second, the requirements for orbit, attitude, and maneuver burn performances were simultaneously estimated and analyzed to maintain the $1^{st}$ elliptical orbit achieved around the moon within the specified orbital period. Finally, the dispersion requirements on the B-plane aiming at target points to meet the target insertion goal were analyzed and can be utilized as reference target guidelines for a mid-course correction (MCC) maneuver during the transfer. More detailed system requirements for the KPLO mission, particularly for the spacecraft bus itself and for the flight dynamics subsystem at the ground control center, are expected to be prepared and established based on the current results, including a contingency trajectory design plan.