• 한국학교수학회논문집
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• 제10권4호
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• pp.519-533
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• 2007

본 연구에서는 삼각형의 높이 및 내접원의 반지름에 대한 한 등식을 증명하기 위한 다양한 탐색수행의 방향을 기술하였고, 이를 바탕으로 등식에 대한 다양한 증명방법을 제시하였다. 이를 통해, 체계적인 탐색수행을 통한 다양한 풀이방법 발명의 한 예를 제시하였으며, 다양한 풀이방법에 대한 수학교수학적 논의의 방향과 폭을 확장시킬 수 있는 기초 자료가 될 것으로 기대된다.

• 대한기계학회논문집B
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• 제32권5호
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• pp.392-399
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• 2008

Accurate measurement of speed and altitude of flying vehicles in air data system remains a critical technical issue. A highly reliable Pitot-static probe is required to obtain air data such as total pressure and static pressure. In this study, an analysis of the characteristics of flowfield around the Pitot-static probe was performed by using a Navier-Stokes CFD code. In addition, for the purpose of finding an optimal configuration, a technique based on the response surface method is applied to the problem with design parameters including shape of the nose section and cone angle. It is shown that the optimal configuration fulfills the MIL specification in wider range of high angles of attack.

• 항공우주시스템공학회지
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• 제14권4호
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• pp.1-9
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• 2020

The characteristics of an aerospike pintle nozzle system with excellent altitude compensation were analyzed using cold air testing. It was confirmed that reducing the stroke of the aerospike nozzle is effective in increasing the thrust. However, the results of additional numerical analysis indicated that the discharge coefficient factor was significantly lower at the maximum stroke. The Vena contracta due to the cowl reduction angle decreased the effective nozzle throat area at the maximum stroke and hindered expansion. Complementing the cowl design may thus increase the efficiency of a solid-propellant rocket engine that uses the aerospike pintle nozzle system.

• 한국군사과학기술학회지
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• 제9권2호
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• pp.143-151
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• 2006

This paper investigates effects of reaction control jet on the aerodynamic performance of generic interceptor missile operating at supersonic flight condition. Parallelized CFDS code is used as a viscous flow solver. The generic interceptor missile configuration composed of a long and slender body and fixed tail fins. The behavior of normal force, axial force and pitching moment characteristics at altitude conditions corresponding to 10 km is studied according to the given control jet conditions, different angle of attacks based on the analysis of aerodynamic characteristics.

• 대한원격탐사학회지
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• 제25권3호
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• pp.287-294
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• 2009

KOMPSAT-2 like other high-resolution satellites has the time and angle difference in the acquisition of the panchromatic (PAN) and multispectral (MS) images because the imaging systems have the offset of the charge coupled device combination in the focal plane. Due to the differences, high altitude and moving objects, such as clouds, have a different position between the PAN and MS images. Therefore, a mis-registration between the PAN and MS images occurs when a registration algorithm extracted matching points from these cloud objects. To overcome this problem, we proposed a new registration method. The main idea is to discard the matching points extracted from cloud boundaries by using an automatic thresholding technique and a classification technique on a distance disparity map of the matching points. The experimental result demonstrates the accuracy of the proposed method at ground region around cloud objects is higher than a general method which does not consider cloud objects. To evaluate the proposed method, we use KOMPSAT-2 cloudy images.

• 한국군사과학기술학회지
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• 제22권5호
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• pp.590-598
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• 2019

Aerial photographs taken by an image sensor fixed on a flight body, e.g. without a gimbal, are generally distorted according to its attitude, altitude and angle of view in flight. This can result in a significant difficulty of analyzing geometric information which should be integrated for numerous still frames. In this study, a simulation method of observation performance that uses geometric relationships between navigation data and image data is suggested, and this method is shown to be very useful for easily examining the integrated information such as the total range of photography, the time of target acquisition, etc.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.452-455
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• 2008

Model Scramjet engine is tested with T4 free-piston shock tunnel at University of Queensland, Australia. Basically, test condition is fixed as Mach 7.6 at 31 km altitude. With this condition, variation effects of fuel equivalence ratio, cavity, cowl setting and angle of attack were investigated. In the results, supersonic combustion was observed with low and middle fuel equivalence ratio. At high equivalence ratio, thermal choking was occurred due to the intensive reaction. Cavity and W-shape cowl showed early ignition and enhanced mixing respectively.

• International Journal of Computer Science & Network Security
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• 제21권12호
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• pp.93-100
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• 2021

Satellite communication for high altitude platform stations (HAPS) and geostationary orbit (GEO) systems suffers from sand and dust (SANDU) storms in desert and arid regions. The focus of this paper is to propose common relations between HAPS and GEO for the atmospheric impairments affecting the satellite communication networks operating above Ku-band crossing the propagation path. A double phase three-dimensional relationship for HAPS and GEO systems is then presented. The comparison model present the analysis of atmospheric attenuation with specific focus on sand and dust based on particular size, visibility, adding gas effects for different frequency, and propagation angle to provide systems' operations with a predicted vision of satellite parameters' values. Thus, the proposed system provides wide range of selecting applicable parameters, under different weather conditions, in order to achieve better SNR for satellite communication.

• 전자공학회논문지D
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• 제35D권9호
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• pp.1-12
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• 1998

표적의 방위각과 거리, 고도 정보를 실시간으로 검출하는 3차원 위상 배열 레이다용 수신기를 제작하였다. 이는 수신기 보호 기능과 감도를 제어하는 초고주파수부와 중간주파수부, 모노펄스 검출기, IQ 위상 검출기, 자동이득 제어부, 수신장치 제어기 등으로 구성되었으며, 동일 표적에 의해 반사된 두 반향 신호의 진폭을 비교하여 고도각 정보의 정확성을 높이기 위해 같은 기능의 2채널 수신기를 구현하였다. 수신기의 TSS 감도는 -98dBm, 수신기의 대역폭은 500MHz, 수신기 전체 이득은 최대 100dB까지 제어가능하며(AGC off시 수동으로), 두 채널간 이득 불균형은 최대 5dB이며, 위상 불균형은 최대 30°이다. 위상 검출기의 이미지 억제율은 평균 30dB이다. 수신기는 패키지 형태의 부품을 고유전율 기판에 실장하여 구현하였다.

• 한국항공우주학회지
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• 제39권10호
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• pp.927-934
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• 2011

상승 비행에 의해 위치에너지를 축적하는 태양동력 장기체공 무인기에 대하여 설계 인자 분석을 수행하였다. 위치에너지 축적을 위한 비행과 관련된 인자인 최저 및 최고 수평 비행 고도, 활강 및 상승 각도, 설계점 속도 및 고도, 활강 및 상승 시작 시각을 분석 대상으로 하였다. 태양동력 무인기 구성품의 중량 모델을 이용하여 항공기 크기 및 중량을 결정하고 비행 중 생산 및 소모하는 에너지를 계산함으로써 임무 수행에 필요한 배터리 용량을 결정하였다. 각 설계 인자값과 무인기 중량의 관계를 연구하였다. 최고 수평 비행 고도, 활강 및 상승 각도, 설계점 속도 및 고도, 활강 및 상승 시작 시각에는 설계가 가능하도록하는 범위가 존재하며 이 범위 내에서 총 중량을 최소화하는 최적값이 존재하였다.