• The Proceedings of the Korean Institute of Illuminating and Electrical Installation Engineers
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• v.10 no.6
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• pp.96-103
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• 1996

This paper describes the electron transport characteristics in SF6 gas calculated for range of E/N values from 150~ 800[Td) by the Monte Carlo simulation and Boltzmann equation method using a set of electron collision cross sections detennined by the authors and the values of electron swarm parameters are obtained by TOF method. The results gRined that the values of the electron swarm parameters such as the electron drift velocity, the electron ionization or Rttachment coefficients, longitudinal and transverse diffusion coefficients agree with the experimental and theoretical for a range of E/N. The properties of electron avalanches is concerned electron energy non--equilibrium region. The electron energy distributions function were analysed in sulphur hexafluoride at E/N : 500~800[Td) for a case of non-equilibrium region in the mean electron energy. The validity of the results obtained has been confilll1ed by a TOF method.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.4
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• pp.43-52
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• 2004

In this paper, the performance of the KOMPSAT-1 orbit determination (OD) accuracy at the ground station was analyzed by using the flight data. The Bayesian least squares estimation was used for the orbit determination and the assessment of the orbit accuracy was evaluated based on orbit overlap comparisons. We also compared the result from OD using GPS navigation solutions with NORAD TLE and the result from OD using range data. Furthermore, the effect of observation type and OBT drift on the accuracy was investigated. As a consequence, It is shown that the OD accuracy using only GPS position data is on the order of 5m RMS (Root Mean Square) with 4 hrs arc overlap for the 30hr arc and the GPS velocity data is not proper as a observation for the OD due to its inferior quality. The significant deterioration of the accuracy due to the critical clock bias was not founded by means of the comparison of OD result from other observations.

• Journal of Advanced Navigation Technology
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• v.15 no.3
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• pp.412-418
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• 2011

In the airport, digital signage is used to provide the flight-related information for the passengers. Because the current digital signage is based on wired networking or storage medium, its use is limited in terms of the location and the usage of the digital signage. In order to overcome these limitation, we present a WiBro-based digital signage for the wireless broadband networking and the mobility of the digital signage. We perform comparative experiments with the WiBro-based digital signage and WLAN-based digital signage under various locations, datarate, advertisement contents. The experimental results showed that the WiBro-based digital signage is preferred when the mobility is required, while the WLAN-based digital signage has advantage in datarate.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.7
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• pp.574-580
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• 2017

Static dischargers should be installed on air vehicle to emit a static electricity during flight. Especially, If static electricity is not removed by static discharger on the air vehicle, it makes ionization and corona effect on the edge of antenna and wing. Those phenomenon bring about performance degradation for radio communication and equipment operation. In this paper, the conditions such as climate, air vehicle's speed and frontal area were analyzed to design static dischargers. As a result, the static dischargers would be optimally designed for air vehicles and the performance of the static dischargers can verify according to the functional experiment. Therefore the result of this research will be used to make static discharger installation design for new air vehicle that have different size and mission.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.23 no.1
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• pp.47-55
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• 2012

This paper describes the developed HILS and test equipment in order to test the performances of MMW(Millimeter-Wave) seeker which can detect and track a high speed of short-range ballistic missile and aircraft. This system is used to 141 horn antenna array, array switching, and gain and phase control algorithm to simulate various kind of targets and trajectory of high speed and maneuver moving target. In addition, it simulates not only velocity and range for these targets but also clutter and jamming environments. System configuration and implementation and the measurement results of major subsystems such as target motion simulator, simulation signal generator, high speed data aquisition unit, and central control unit are presented. These systems could verify the detection and tracking performance of MMW seeker through dynamic real-time test based on simulation flight scenario.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.11
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• pp.849-859
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• 2020

The semi-empirical equation and commercial computational tool were used to predict the base drag of a guided missile with free-stream Mach numbers and chamber pressures, and the results were generally agree each other. Differences in flow characteristics and base drags were observed with over/under expansion conditions by the nozzle. Under the over-expansion condition, the base pressure decreased as the expansion fan was generated at upper region of the base, and base pressure decreased further with increasing free-stream Mach number as the expansion becomes strong. Under the under-expansion conditions, a shock wave was generated around the base by the influence of the nozzle flow, which increased the base pressure, and the effect increased as the chamber pressure increased. Under the same chamber pressure condition, as the free-stream Mach number increases, the characteristic that the base pressure decreases as the shock wave generated at the base moves downstream was observed.

• 한국지형공간정보학회:학술대회논문집
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• 2002.03a
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• pp.145-149
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• 2002

CORONA는 미국이 1960년에서 1972년까지 냉전시대 관심지역에 대한 첩보영상을 취득하기 위하여 운영한 영상취득시스템으로 1995년 일반에 자료가 공개됨에 따라 과거의 고해상도 영상자료를 이용할 수 있는 길이 열리게 되었다. 그러나 현재까지 CORONA 영상처리를 위한 모듈을 제공하는 원격탐측 소프트웨어가 개발되어 있지 않기 때문에 CORONA 영상을 이용하여 수치표고모형이나 정사영상을 제작하기 위해서는 적절한 모델링 방법이 필요하다. CORONA 영상은 파노라마 영상으로 필름 가장자리로 갈수록 왜곡이 많이 생기며 사진기 지표가 없고 위성의 궤도와 위치, 자세, 속도, IMC(Image Motion Compensation)에 대한 자세한 자료를 제공하지 않는 문제점이 있다. 따라서 본 논문에서는 지형복원을 위하여 지상기준점을 이용하는 2가지 모델링 방법을 이용하였다. 첫 번째는 파노라마 왜곡과 촬영 비행체 이동에 의한 왜곡, IMC에 의한 왜곡을 보정하는 모형식을 구성하여 이용하였으며, 두 번째는 위성과 센서에 대한 정보를 필요로 하지 않는 다항식비례모형(RFM; Rational Function Model)을 이용하였다. 대상지역은 서울지역의 입체영상으로 대략 $33km{\times}26km$ 지역이다. 영상은 지상해상도 약 2.7m로 스캐닝하였고 1:1000 수치지도를 통해 20개의 기준점과 36개의 검사점을 관측하였다. 검사점의 위치정확도를 평가해 본 결과 첫 번째 방법은 수평방향으로 평균 3.9m(X), 2.8m(Y)의 오차를 보였으며 표고의 경우 4.2m의 오차를 보여주었다. 두 번째 방법은 수평방향으로 평균 3.2m(X), 2.8m(Y)의 오차를 보였으며 표고의 경우 5.5m의 오차를 보여주었다. 지형복원 정확도를 검증하기 위하여 첫 번째 방법을 이용하여 대상지역 중 일부인 서울 남산지역에 대해 정사영상과 10m간격의 DEM을 제작하였으며 1:1000 수치지도를 통해 제작된 DEM과 비교한 결과 총 43990개 격자점의 표고 차이는 평균 5.98m였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.1
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• pp.12-20
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• 2002

An integrated analysis of kerosine/LOX based KSR-III rocket body/plume flowfield has been performed. The analysis has been executed employing three kind of gas thermo-chemical models including calorically perfect gas, multiple species chemically reacting gas, and chemically frozen gas models and their effect on rocket flowfield has been accessed to provide the most appropriate gas thermo-chemical model which meets a specific purpose of performing rocket body and plume analysis. The finite-rate chemically reacting flow solution exhibited higher temperature throughout the flowfield than other gas models due to the increased combustion gas temperature caused by the chemical reactions within the nozzle. All the reactions were dominated only in the shear layer and behind the barrel shock reflection region where the gas temperature is high and the effect of finite-rate chemical reactions on the flowfield was found to be minor. However, the present plume computation including finite-rate chemical reactions revealed major reactions occurring in the plume and their reaction mechanisms and as well.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.290-293
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• 2017

A direct-connected, continuous type combustion test facility was developed to test a supersonic combustor model used in scramjet engines. The facility requirements were determined by assuming the flight speed of Mach 5, yielding the combustor inlet flow speed of Mach 2. Also the cross-section of the supersonic combustor under test was assumed as $32mm{\times}70mm$. As a result, the facility was designed to have the flow total pressure of 548 kPaA, total temperature of 1,320 K, and flow rate of 0.776 kg/s. The facility consists of a turbo type air compressor, electric air heater, vitiation air heater and a two dimensional facility nozzle to accelerate the flow to Mach 2. Also, an oxygen supply system was added to compensate the vitiation. The exhaust de-pressurization system is not added. Designed pressure, temperature, and flow rate were verified through the test operation of the facility.

• Analytical Science and Technology
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• v.18 no.6
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• pp.483-490
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• 2005

Mass resolution of the time of flight aerosol mass spectrometer for an aerosol component analysis depends on the initial direction and the initial energy of the ions. We have found that the shape of the optimum post focusing electric field is not linear. The maximum electric potential should be applied to the ions whose initial direction is 90 degree. To check on the post focusing effects, we have installed a laser ablation mass spectrometer. By using this LA-MS, we have found that the average energy distribution of the laser ablated ions is 8 eV. To establish the optimum mass resolution, a time delay and a high voltage are needed, and the results of the study show that 1500 nsec, and 3.7 kV are the optimum parameters for our system respectively. The isotope mass signals of copper show a good resolution.