• 항공우주시스템공학회지
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• 제7권3호
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• pp.33-38
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• 2013

The air data measured from the static pressure, the dynamic pressure and etc. of an airplane is used for calculation of many flight parameters(altitude and airspeed and so on) and these values applied to flight safety and navigation flight. The pitot-static system of the development airplane is calibrated by finding of pitot-static system's error using tower fly-by, trailing cone method and etc. This paper is describing for the introduction of the trailing cone method and major items for test planning, preparation, operation and results for air data calibration flight test performed, considering efficiency and safety during KC-100 development project.

• 천문학논총
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• 제13권1호
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• pp.65-73
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• 1998

We installed windscreen at the BOAO 1.8m telescope dome, in order to reduce the degradation of image Quality under strong wind larger than 8m/sec. The windscreen was designed on the basis of that installed at the MSSSO 2.3m telescope dome in Australia. We developed control system (remote control and user program) of the windscreen, being able to operate the windscreen at observation room. We tested the performance of the windscreen under strong wind of 6-15m/see. Tracking error of the telescope, especially in altitude-axis, was greatly decreased when the windscreen was used. Standard deviation of the error was estimated to be less than 0.3arcsec, which has little effect on image quality.

• 제어로봇시스템학회논문지
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• 제8권11호
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• pp.984-990
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• 2002

We propose a new type of nonlinear fixed interval smoother to which an existing nonlinear smoother is modified. The nonlinear smoother is derived from two-filter formulas. For the backward filter. the propagation and the update equation of error states are derived. In particular, the modified update equation of the backward filter uses the estimated error terms from the forward filter. Data fusion algorithm, which combines the forward filter result and the backward filter result, is altered into the compatible form with the new type of the backward filter. The proposed algorithm is more efficient than the existing one because propagation in backward filter is very simple from the implementation point of view. We apply the proposed nonlinear smoothing algorithm to off-line navigation system and show the proposed algorithm estimates position, and altitude fairly well through the computer simulation.

• 한국항공운항학회지
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• 제28권4호
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• pp.47-54
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• 2020

This study carries out a basic study of ways to calculate navigation errors for aircraft operating in the unmanned aerial system traffic management(UTM). Recently, research by UTM has been carried out both at home and abroad, along with the initial study of system definitions at the basic stage, operational techniques of the aircraft, and the practicality of the concept of necessary operations at the actual operational stage. This study presented after a review the factors that should be considered for the calculation of navigation errors among the factors that examine whether the actual low altitude aircraft can operate properly within UTM during its actual operation and the need to apply them in practice.

• 대한공간정보학회지
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• 제23권1호
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• pp.55-63
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• 2015

최근 부동산거래의 투명성과 공평과세의 기반을 마련하고자 부동산 실거래가격의 활용에 대한 필요성이 증가하고 있다. 본 연구는 부동산 실거래가격의 활용과정에서 실거래 미발생지점에 대한 효과적인 가격추정을 위해 실거래 가격 및 고도, 경사도를 통합한 공동크리깅의 적용 가능성을 연구하였다. 이를 위해 경북 영천시의 2012년 1월부터 2014년 6월까지의 실거래 자료를 활용하여 실거래가격을 추정하였으며, 이를 정규크리깅 추정결과와 비교하였다. 추정된 가격과 2,575개 검증 지점의 실거래가격 사이 평균 오차, 평균제곱근오차 등을 분석한 결과 정규크리깅에 비해 공동크리깅 결과가 실거래가 추정과 현실화 측면에서 모두 효과적인 것으로 나타났다. 이는 지가형성에 영향을 미치는 고도, 경사 등의 영향요인이 고려되는 공동크리깅이 실거래가 추정에서 더 효과적임을 보여준다.

• 제어로봇시스템학회논문지
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• 제22권1호
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• pp.24-30
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• 2016

The accuracy of small and low-cost CCD cameras is insufficient to provide data for precisely tracking unmanned aerial vehicles (UAVs). This study shows how a quad rotor UAV can hover on a human targeted tracking object by using data from a CCD camera rather than imprecise GPS data. To realize this, quadcopter UAVs need to recognize their position and posture in known environments as well as unknown environments. Moreover, it is necessary for their localization to occur naturally. It is desirable for UAVs to estimate their position by solving uncertainty for quadcopter UAV hovering, as this is one of the most important problems. In this paper, we describe a method for determining the altitude of a quadcopter UAV using image information of a moving object like a walking human. This method combines the observed position from GPS sensors and the estimated position from images captured by a fixed camera to localize a UAV. Using the a priori known path of a quadcopter UAV in the world coordinates and a perspective camera model, we derive the geometric constraint equations that represent the relation between image frame coordinates for a moving object and the estimated quadcopter UAV's altitude. Since the equations are based on the geometric constraint equation, measurement error may exist all the time. The proposed method utilizes the error between the observed and estimated image coordinates to localize the quadcopter UAV. The Kalman filter scheme is applied for this method. Its performance is verified by a computer simulation and experiments.

• Journal of Astronomy and Space Sciences
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• 제34권2호
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• pp.127-138
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• 2017

The current study designs the mission orbit of the lunar CubeSat spacecraft to measure the lunar local magnetic anomaly. To perform this mission, the CubeSat will impact the lunar surface over the Reiner Gamma swirl on the Moon. Orbit analyses are conducted comprising ${\Delta}V$ and error propagation analysis for the CubeSat mission orbit. First, three possible orbit scenarios are presented in terms of the CubeSat's impacting trajectories. For each scenario, it is important to achieve mission objectives with a minimum ${\Delta}V$ since the CubeSat is limited in size and cost. Therefore, the ${\Delta}V$ needed for the CubeSat to maneuver from the initial orbit toward the impacting trajectory is analyzed for each orbit scenario. In addition, error propagation analysis is performed for each scenario to evaluate how initial errors, such as position error, velocity error, and maneuver error, that occur when the CubeSat is separated from the lunar orbiter, eventually affect the final impact position. As a result, the current study adopts a CubeSat release from the circular orbit at 100 km altitude and an impact slope of $15^{\circ}$, among the possible impacting scenarios. For this scenario, the required ${\Delta}V$ is calculated as the result of the ${\Delta}V$ analysis. It can be used to practically make an estimate of this specific mission's fuel budget. In addition, the current study suggests error constraints for ${\Delta}V$ for the mission.

• 한국산학기술학회논문지
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• 제11권9호
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• pp.3161-3167
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• 2010

제어를 위한 기구부의 위치 정보는 BLDC 모터의 홀센서를 이용하여 정확한 위치 및 속도제어가 가능하도록 알고리즘을 구현하였으며, 실제 기구부의 방위각과 고도각에 대한 제어 정밀도를 측정한 결과 최대 $2.02^{\circ}$, $1.01^{\circ}$. 오차범위 $1.86^{\circ}$이내로 비교적 정확하였다. 태양광 발전 모니터링 시스템은 LCU를 중심으로 한 통합 모니터링 제어 시스템으로 모든 장비들은 1:N 방식으로 다중 동시접속이 가능하고, 원격지에서 시스템의 제어 및 현재 상태에 대한 실시간 감시가 가능하도록 개발하였다.

• 한국태양에너지학회 논문집
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• 제32권3호
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• pp.104-113
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• 2012

A set of candela distribution curves(CDCs) were generated for a fiber optic dish daylighting system by Photopia under clear sky conditions at different solar altitudes. The candela distribution curves were then exported to Radiance for photometric analysis of a windowless lecture room. Observations were made on the Radiance rendered illuminance images, which provided photo realistic scenes varying with solar altitudes. If no tracking error were assumed, the daylight collection efficiency of the system remained at a constant value of 68.4% during its operation. Higher the solar altitude angle, greater in photometric quantities were observed, which are represented by candela(cd) and total lumens(lm). In all cases considered, however, the angle of light distribution remained fixed reflecting the solar tracking feature of the system. The illuminance uniformity on the workplane lingered around 0.12, which is quite low. This is quite a contrast to its average value of 0.68 of the $2.7m^2$ area directly below the terminal device (diffuser) of the system. The maximum illuminance of 1,340lux was obtained at a solar altitude of 80 degrees.

• 한국산학기술학회논문지
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• 제11권7호
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• pp.2334-2340
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• 2010

Michalsky의 방위각, 고도각, 일출/일몰시각에 대한 태양위치 계산은 국립천문대의 태양위치 정보와 비교했을 때, 최대 각각 $1.5^{\circ}$, $0.88^{\circ}$, 2분 이내의 오차로서 비교적 정확하였다. 현재 시각과 설치위치(경도, 위도)에 대하여 BLDC 모터-실린더를 구동하여 홀센서 위치 피드백으로 Michalsky의 계산식의 태양의 고도각과 방위각을 제어하는 양축 태양광 추적장치를 개발하였다. BLDC 모터의 사용으로 유지보수가 우수하며, 홀센서로 위치피드백으로 모터의 정밀한 위치결정제어가 가능하며, 또한 원점복귀기능으로 누적 오차를 최소화한다.