• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.4
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• pp.318-327
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• 2017

Synthetic Aperture Radars (SARs) that can be performed regardless of weather and day-and-night conditions have been developed for Earth remote sensing in recent decades. Korea Aerospace Research Institute (KARI) has developed and launched successfully the KOrea Multi-Purpose SATellit-5 (KOMPSAT-5) which is the first Korean SAR satellite in 2013, and is currently developing the KOMPSAT-6 which is the next generation series of the SAR satellite. This paper describes the development of the system performance analysis simulator which is necessary for spaceborne SAR payload design and analysis. The system performance analysis simulator consists of the antenna pattern generation simulator, the SAR performance analysis simulator, and the image quality analysis simulator. The simulation results of this research show that this simulator can be applicable as the design and analysis tool for the spaceborne SAR payload system during the design phase.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.163.1-163.1
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• 2012

이 연구는 우주물체에 대한 광학감시 및 추적을 수행하기 위한 선행연구로, 궤도전파 시뮬레이터를 개발하여 궤도상 위성의 광학관측가능성을 분석하고 광학관측 여부를 판단하는 것을 목표로 한다. 연구의 주 내용은 주어진 궤도정보를 바탕으로 하는 태양동기궤도(Sun-Synchronous Orbit; SSO) 위성, Dawn-dusk 위성, 저궤도(Low Earth Orbit; LEO) 위성, 정지궤도(Geostationary Orbit; GEO) 위성 등 궤도상 위성의 추정궤도 전파와 자국위성의 광학관측가능성 분석으로 구성된다. 각각의 궤도전파 정밀도 및 광학관측가능성 분석성능을 확인하기 위해 AGI(Analytical Graphics Incorporated)사의 STK(Satellite Tool Kit) 시뮬레이션 프로그램을 사용하여 개발된 궤도전파 시뮬레이터와 비교하였다. 시뮬레이션 과정에서 광학관측의 제한조건을, 지구반영(penumbra)과 태양직사광(direct sun)에서만 관측하며, 고도(elevation angle)의 최소값은 20도, 태양고도(Sun elevation angle)의 최대값은 -10도로 설정하였다. 광학관측이 이루어지는 가상의 관측소는 임의로 선정하였으며, 기본적인 관측시간은 1년으로 잡고, 계절의 변화에 따른 광학관측가능성 궤적의 변화를 보기위해 춘하추동에 대해서 각각 3일이내의 기간 동안 시뮬레이션을 수행하였다. 결과적으로, 우주물체 광학감시 및 추적을 수행하기 위한 광학관측가능성 분석성능은 궤도전파 시뮬레이터 및 초기궤도요소 정밀도, 좌표변환과정 오차 등의 영향을 받으며, 설정된 제한조건에 따라 광학관측 지속시간의 차이가 발생한다. 연구결과를 통해 궤도상 위성의 궤도를 추정하기 위한 위성의 궤도전파 시뮬레이터를 개발하고, 자국위성의 관측가능성 분석을 통해 광학감시 및 추적시스템의 운영이 원활히 이루어질 수 있도록 한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.1
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• pp.39-47
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• 2008

Automatic landing performance of UAV can be enhanced by adding Pseudolite(PL) to GPS. However, it is very hard to install and operate PL with confidence because GPS satellites are moving and the landing zone are usually changeable. The coverage and accuracy of combined GPS and PL can be estimated by using simulator and the correct information is very crucial to UAV operation. In this paper, design, implementation and evaluation of GPS/PL simulator for UAV landing are given. A very realistic coverage estimation is obtained using GIS data and ray launching method with considerations of the transmitter power level, altitude of UAV, number and location of PL. The expected accuracy is estimated using DOP and NSP computed using both GPS and PL. The performance of simulator is evaluated by comparing with the results of a real GPS receiver, and the certified simulator shows the required accuracy for UAV landing can be easily met by proper installation of at least 2 PLs.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.6
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• pp.608-615
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• 2008

Recently, research on GNSS signal receiver, aiding system and integrated navigation system approaching to the new satellite navigation system is needed. It it necessary to develop the GNSS simulator not only to understand the new satellite navigation system but also to develop the core technology about the system. In this paper, the simulator of the GPS and Galileo satellite nagivation is developed in IF(intermediate frequency) signal level.

• 한국지형공간정보학회:학술대회논문집
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• 2002.03a
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• pp.99-105
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• 2002

컴퓨터의 성능향상으로 인하여 가상현실 및 시뮬레이션에 대한 관심이 급증하고 있다. 본 연구는 차량의 실시간 운전시뮬레이터 개발을 위한 인공위성영상의 적용에 관한 연구이다. 차량의 효율적인 성능테스트나 주행테스트를 위해서는 자동차공학과 토목공학의 접목이 필요하며, 그래픽 처리 분야에서는 가상 그래픽 주행 시뮬레이터 프로그램(Virtual Driving Simulator ; VDS) 개발, 실시간 그래픽 처리를 위한 알고리즘 개발, 효율적인 환경 및 차량 모델링 생성 및 관리 방법 개발, 인체 모델 시뮬레이션 및 설계 검증 기능부여, 가상현실 기법을 도입한 인간-컴퓨터 인터페이스를 구성 및 평가 등을 실시해야한다. 차량의 주행감각 등 가상 실험을 수행할 수 있는 독자적인 차량의 실시간 주행 시뮬레이터개발과 현실감을 부여할 수 있는 제어 알고리즘 개발, 주행 시뮬레이터의 개발을 위한 각종 인터페이스 구축에 이용되는 위성영상의 활용방안과 효용성에 관한 연구와 워크스테이션과 개인용PC에서의 실시간 시뮬레이션 구축에서의 렌더링의 상관관계 등을 분석하였다.

• Journal of Satellite, Information and Communications
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• v.6 no.1
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• pp.50-56
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• 2011

During the development of flight software, the processor emulator and satellite simulator are essential tools for software development and verification. SWT/KARI developed the software-based spacecraft simulator based on TSIM-ERC32 processor emulator from Aeroflex Gaisler. But when developing flight software using TSIM-ERC32, there are much limitation for understanding of exact behavior of ERC32 processor, and it is impossible to change or modify the emulator core to develop the satellite simulator. To reslove this problem, this paper presents the development of new cycle-true ERC32 emulator as laysim-erc32 and describes the software development and debugging method on VxWorks/RTEMS RTOS.

• Journal of Satellite, Information and Communications
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• v.5 no.2
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• pp.1-7
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• 2010

For many years the development and verification of on-board flight software have been essentially performed on STB (Software Test Bed) environments which consist of real hardware in KARI. During development of on-board flight software on STB, we experienced many difficulties such as the late delivery of target hardware and limitation to access STB simultaneously by multiple developers. And it takes too much time and cost to build up multiple STBs. In order to successfully resolve this kind of problems, the software-based spacecraft simulator has been developed. The simulator emulates the on-board computer, I/O modules and power controller units and it supports the debugging and test facilities to software engineers for developing flight software. Also the flight software can be loaded without any modification and can be executed as pseudo real-time. This paper presents the architecture and design of software-based spacecraft simulator, and flight software development and verification under this environment.

• Journal of Astronomy and Space Sciences
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• v.20 no.4
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• pp.339-350
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• 2003

Engineering qualification model payload for a communications and broadcasting satellite(CBS) was developed by ETRI from May, 2000 to April, 2003. For. the purpose of functional test and verification of the payload, a real-time hardware-in-the-loop(HITL) CBS simulator(CBSSIM) was also developed. We assumed that the spacecraft platform for the CBSSIM is a geostationary communication satellite using momentum bias three-axis stabilization control technique based on Koreasat. The payload hardware is combined with CBSSIM via Power, Command and Telemetry System(PCTS) of Electrical Ground Support Equipment(EGSE). CBSSIM is connected with PCTS by TCP/IP and the payload is combined with PCTS by MIL-STD-1553B protocol and DC harness. This simulator runs under the PC-based simulation environment with Windows 2000 operating system. The satellite commands from the operators are transferred to the payload or bus subsystem models through the real-time process block in the simulator. Design requirements of the CBSSIM are to operate in real-time and generate telemetry. CBSSIM provides various graphic monitoring interfaces and control functions and supports both pre-launch and after-launch of a communication satellite system. In this paper, the HITL simulator system including CBSSIM, communications payload and PCTS as the medium of interface between CBSSIM and communications payload will be described in aspects of the system architecture, spacecraft models, and simulator operation environment.

• Proceedings of the Korea Information Processing Society Conference
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• 2008.05a
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• pp.491-492
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• 2008

인공위성에 탑재되는 S/W는 위성 내의 다양한 장치들과 유기적으로 통신하며 위성의 동작을 제어하고 임무를 수행한다. 따라서 이들 장치들과의 상호 작용이 충분히 테스트되어야 하나, S/W 개발 과정에서 해당 장치들과 직접 연동되어 개발하기 어려운 경우가 대부분이다. 이에 위성에 탑재되는 다른 장치 및 탑재체의 기능과 역할을 모사할 수 있는 시뮬레이터가 필요성이 대두된다. 본 연구에서는 Java를 이용한 시뮬레이터 개발 방안에 대하여 소개한다.

• Aerospace Engineering and Technology
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• v.11 no.2
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• pp.129-139
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• 2012

This paper will describe the structure and characteristics of operator training system which was developed to maintain the quality of operational ability for COMS (Communication, Ocean and Meteorological Satellite) operators during a long-term nominal operations of missions and a contingency operations against an occurrence of anomaly. In particular it will present benefits and expected effects of the training system with a focus on three parts which are functions especially for trainer-friendly failure injection, an automatic sequencer of training scenario based on the predefined plan and additional functions of the existing COMS simulator. Furthermore, it will present a practical example of training on the training system to understand the overall mechanism of training process.