• 한국항공우주학회지
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• 제36권2호
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• pp.105-114
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• 2008

본 연구에서는 고정익과 회전익의 두 가지 모드로 운용되는 canard rotor wing(CRW) 항공기에 대한 사이징과 성능해석 프로그램이 개발되었다. 개발된 프로그램은 기존의 항공기 데이터를 이용하여 각 모드에 대한 검증을 수행하였고 정찰 임무형상에 대해 최적설계 문제를 정의하였다. canard rotor wing의 로터 최적화를 위해 고정익 모드와 회전익 모드에 대해 가중치를 이용한 다중목적함수를 구성하였다. 6개의 서로 다른 가중치와 설계제약조건에 대해 최적설계가 수행되었고 그 결과 개선된 로터형상을 도출하였다.

• Korean Journal of Geomatics
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• 제3권1호
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• pp.59-65
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• 2003

The merging of different scales or multi-sensor image data is becoming a widely used procedure of the complementary nature of various data sets. Ideally, the merging method should not distort the characteristics of the high-spatial and high-spectral resolution data used. To present an effective merging method for survey of reclaimed land using the high-resolution (6.6 m) Electro-Optical Camera (EOC) panchromatic image of the first Korea Multi-Purpose Satellite 1 (KOMPSA T-l) and the multispectral Moderate Resolution Imaging Spectroradiometer (MODIS) image data, this paper compares the results of Intensity Hue Saturation (IHS) and Principal Component Analysis (PCA) methods. The comparison is made by statistical and visual evaluation of three-color combination images of IHS and PCA results based on spatial and spectral characteristics. The use of MODIS bands 1, 2, and 3 with a contrast stretched EOC panchromatic image as a substitute for intensity was found to be particularly effective in this study.

• 한국멀티미디어학회논문지
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• 제20권4호
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• pp.593-605
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• 2017

In applications which are covered wide range, it is possible that one or more number of Unmanned Aerial Vehicle(UAV) squadrons are used to perform a mission. In this case, it is most important to communicate seamlessly between the UAV squadrons. In this paper, we applied the modified OLSR(OSLR-Pds) which can prediction for state of the link for the communication in UAV squadron, and applied the modified AOMDV which can build multi-path for the communication between UAV Squadrons. The mobility of nodes are modeled using Gauss-Markov algorithm, and relative speed between nodes were calculated by derive equation of movement, and thereby we can predict link state for in a squadron and between squadrons. An experiment for comparing AODV, AOMDV and the proposed routing protocol was conducted by three factors such as packet delivery ratio, end to end delay, and routing overhead. In experiment result, we make sure that the proposed protocol performance are superior in these three factors. However, if the density of the nodes constituting FANET are too low, and if the moving speed of node is very slow, there is no difference to others protocols.

• 항공우주기술
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• 제12권1호
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• pp.144-151
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• 2013

다목적실용위성 2호(이하 KOMPSAT-2)는 고해상도 1.0m 흑백영상을 촬영할 수 있는 PAN 카메라와 4.0m 다중파장대의 칼라 영상을 수집할 수 있는 멀티스펙스럴 카메라를 탑재하고 있다. 이를 통하여 취득한 위성영상은 국토관리, 농업, 환경, 해양감시 및 GIS등의 광범위한 분야에 활용되고 있다. 본 연구는 KOMPSAT-2 자료를 이용하여 지상좌표를 해석하는 방법과 해석된 지상좌표의 위치정확도를 KOMPSAT-2 시스템 요구사항인 위치정확도를 만족시키기 위해 현재 적용되고 있는 위치정확도 보정계수 산출절차를 정의하는 것을 목적으로 한다.

• 한국군사과학기술학회지
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• 제5권2호
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• pp.72-82
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• 2002

This paper presents the design technology of a Graphic Generator which drives the embedded aircraft display equipments such as HUD(Head-Up Display) and MFD (Multi-Function Display) those provide pilot with the most important mission information. The main issue of this design is how we can implement the real-time embedded graphic generator using a general purpose processor as a substitute for the obsolete the production of specific graphic processor in the military market. So we proposed two kinds of method that one is a software solution so called graphic kernel system, interpreting the display file, controlling the graphic system and pre-processing graphic primitives, the other is a hardware solution so called graphic engine, interpreting passed commands through the graphic kernel system, post-processing the looping calculation taking much of time as implemented by software. We have tested and verified the functionalities and the required performance of Graphic Generator.

• 한국군사과학기술학회지
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• 제13권4호
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• pp.708-715
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• 2010

In Strapdown Inertial Navigation System, alignment accuracy is the most important factor to determine the performance of navigation. However by an existing self-alignment method, it takes a long time to acquire the alignment accuracy that we want. So, to attain the desired alignment accuracy in as little as $\bigcirc$ minutes, we have developed the precise multi-position alignment method. In this paper, it is proposed a inertial measurement matching transfer alignment method among alignment methods to minimize the alignment error in a short time. It is based on a mixed velocity-DCM matching method be suitable to the operating environment of vertical launching system. The compensation methods to reduce misalign error, especially azimuth angle error incurred by measurement time-delay error and body flexure error are analyzed and evaluated with simulation. This simulation results are finally confirmed by experimentations using FMS(Flight Motion Simulator) in Lab and the integration test to follow the fire control mission.

• 한국산업정보학회논문지
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• 제15권2호
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• pp.17-22
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• 2010

다목적실용위성 2호 (KOMPSAT-2)의 상용화로 인한 국내외 사용자의 요구사항에 부합하는 고품질 위성자료의 처리를 위한 수신과 제품을 생성하기 위한 처리시스템의 기술적인 진보와 해외 위성 직수신 시스템과 연계된 운용을 위해 체계화된 플랫폼의 구성이 요구되고 있다. 더불어 다목적실용위성 3호 및 5호 등 기 개발 중이거나 개발될 시스템의 유사기능의 중복개발 방지와 원활한 시스템 운영을 위해 통합 자료처리 시스템의 필요성이 절실한 때이다. 이에 본 논문에서는 이미 운용중인 다목적실용위성 2호의 자료처리 시스템을 기반으로 하여 향후 다목적실용위성 시리즈의 상용화를 고려해 통합자료처리 시스템의 개념적 설계를 수행해 보았다.

• International Journal of Aeronautical and Space Sciences
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• 제1권1호
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• pp.70-80
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• 2000

The attitude knowledge error model is formulated for specifically KOMPSAT attitude determination system using the Lefferts/Markley/Shuster method, and the attitude determination(AD) error analysis is performed so as to investgate the on-board attitude determination capability of KOrea Multi-Purpose SATellite(KOMPSAT) using the covariance analysis method. Analysis results show there is almost no initial value effect on Attitude Determination (AD) error and the sensor noise effects on AD error are drastically decreased as is predicted because of the inherent characteristic of Kalman filter structure. However, it shows that the earth radiance effect of IR-sensor(earth sensor) and the bias effects of both IR-sensor and fine sun sensor are the dominant factors degrading AD error and gyro rate bias estimate error in AD system. Analysis results show that the attitude determination errors of roll, pitch and yaw axes are 0.056, 0.092 and 0.093 degrees, respectively. These numbers are smaller than the required values for the normal mission of KOMPSAT. Also, the selected on-orbit data of KOMPSAT is presented to demonstrate the designed AD system.

• Journal of Astronomy and Space Sciences
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• 제15권2호
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• pp.437-447
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• 1998

한반도의 지도 제작을 주임무로 1999년에 발사될 다목적 실용위성의 궤도 오차를 GPS 항행 해와 지상 안테나의 추적 데이터를 이용하여 분석하였다. 측정 데이터의 잡음과 모델 링의 오차를 고려하여 최소 자승 방법으로 궤도 결정과 예측 오차를 시뮬레이션 하였다. 측정 데이터의 잡음은 단기간 오차의 주 요인이 되며, 태양 플럭스의 불확실성으로 인한 오차가 궤도 예측 오차에 가장 크게 작용함을 알 수 있었다.

• 한국항공운항학회지
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• 제18권4호
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• pp.1-8
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• 2010

In the aerospace field, the study on a morphing-wing is in progress to improve flight performance and perform multi flight mission. There are many concepts of morphing-wing such as camber-change, wing-twist, variable-span, and so on. In this study, the aerodynamic characteristics and flight control of an air vehicle with a variable-span morphing wing (VSMW) have been investigated. VSMW with symmetric span control(SSC) can increase cruising range of aircraft by reducing drag in various flight condition. VSMW with anti-symmetric span control(ASSC) can be used in the roll control of an aircraft. The flight control about pure rolling dynamic system and full dynamic system have been performed about the cruise missile.