• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
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• pp.304-307
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• 2004

Satellite orbit determination using angles only data from single ground station is carried out. The KOMPSAT-1 satellite mono-pulse angle tracking data from 9-meter S-band antenna at KARI site in Daejeon are used for the orbit determination. Various angle tracking arcs from one-day to five-day are processed and the orbit determination results are analyzed. Antenna pointing data are predicted based on the orbit determination results to check the possibility of re-acquisition and tracking of the satellite signal. Normal satellite mission operations including orbit determination, antenna prediction, satellite re-acquisition and automatic tracking from predicted antenna angle pointing data are concluded to be possible when three-day angle tracking data from single tracking station are used for the orbit determination.

• 한국정보처리학회:학술대회논문집
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• 한국정보처리학회 2016년도 춘계학술발표대회
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• pp.675-678
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• 2016

최근 무인항공기 (Unmanned Aerial Vehicel, UAV)는 장점인 빠른 이동속도와 장착된 카메라를 이용하여 넓은 지역을 감시하기 위해서 활용되고 있다. 하지만, 조종사가 UAV를 직접 조종하여 넓은 지역을 비행하기에는 많은 비용이 발생한다. UAV가 자율적으로 넓은 지역을 비행하는 방법이 요구된다. 이 논문은 웨이포인트를 기반으로 UAV를 비행시키기 위한 Ground Control Station (GCS)의 구조를 제안한다. 비행할 웨이포인트는 위성항법시스템(Global Positioning System, GPS) 기반으로 설정하고 제안한 구조를 기반으로 다양한 임무 수행을 위해 다수의 비행 알고리즘을 정의하여 UAV를 비행시킨다. 부가적으로, 웨이포인트 기반으로 UAV를 비행시키기 위한 사용자 인터페이스도 소개한다.

• 대한전기학회논문지:시스템및제어부문D
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• 제54권8호
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• pp.482-485
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• 2005

STSAT-2 is first satellite which is scheduled to launch by first Korea launcher. Ground station Baseband Controller(GBC) for operating STSAT-2 is now developing. GBC control data flow path between satellite operation computers and ground station antennas and count number of received data packets among demodulated audio signals from three antennas and also set data flow path to good-receiving antenna automatically In GBC two uplink FSK modulators(1.2kbps, 9.6kbps) and six downlink FSK demodulators(9.6kbps, 38.4kbps) are embedded. STSAT-2 GBC hardware is more simpler than STSAT-1 GBC by using FPGA in which all digital logic implemented. Now test and debugging of GBC hardware and Software(FPGA Code and CBC Manager Program) is well progressing in SaTReC, KAIST. This paper introduce GBC structure, functions and test results.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2005년도 심포지엄 논문집 정보 및 제어부문
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• pp.116-118
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• 2005

STSAT-2 is first satellite which is scheduled to launch by first Korea launcher. After launch Ground station Baseband Controller(GBC) for operating STSAT-2 is now developing. GBC control data flow path between satellite operation computers and ground station antennas. and GBC count number of received data packets among demodulated audio signals from three antennas and set data flow path to good-receiving antenna automatically. In GBC two uplink FSK modulators(1.2kbps, 9.6kbps) and six downlink FSK demodulators(9.6kbps, 38.4kbps) are embedded. STSAT-2 GBC hardware is more simpler than STSAT-1 GBC by using FPGA in which all digital logic implemented. Now test and debugging of GBC hardware and Software(FPGA Code and GBC Manager Program) is well progressing in SaTReC, KAIST. This paper introduce GBC structure, functions and test results.

• 제어로봇시스템학회논문지
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• 제11권11호
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• pp.930-935
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• 2005

In this paper, position tracking control of an autonomous helicopter is presented. Combining an LQR method and a proportional control forms a simple PD control. Since LQR control gains are set for the velocity control of the helicopter, a position tracking error occurs. To minimize a position tracking error, neural network is introduced. Specially, in the frame of the reference compensation technique for teaming neural network compensator, a position tracking error of an autonomous helicopter can be compensated by neural network installed in the remotely located ground station. Considering time delay between an auto-helicopter and the ground station, simulation studies have been conducted. Simulation results show that the LQR with neural network performs better than that of LQR itself.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2009년도 제40회 하계학술대회
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• pp.1948_1949
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• 2009

All the power generating station require dc auxiliary power systems to operate those dc components that must be available if a loss of ac power occur. Some examples of such components are auxiliary motors, circuit breakers, relays and solenoids. The dc source may be one common battery for both power and control or two separate batteries; one for power and another for control. Typically, a dc auxiliary power system is designed as an ungrounded system, instead of grounded system, so that a low-resistance ground fault on one of its two polarities will not affect the operation of the system, thus increasing system reliability and continuity of service. A ground detector should provide a high polarity-to-ground resistance so that a single ground fault occurring on the system will not affect the operation of that system. Sensitive relays have been known to energize momentarily while the cable and capacitive charge to ground shifts[1]. A power station had experienced this kind of incident and performed root cause analysis based on PC based simulation program known as PSpice. This simulation showed adapted relays on the system energize momentarily and design criteria on this relay should be corrected.

• 정보처리학회논문지:소프트웨어 및 데이터공학
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• 제6권2호
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• pp.51-56
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• 2017

최근에 증가한 무인항공기(Unmanned Aerial Vehicle, UAV) 활용에 따라 다양한 UAV 제어 방법이 도입되고 있다. 일반적으로는 UAV 조종기를 통해 직접 제어하는 방법이 많이 활용되고 있다. 하지만, 세밀한 UAV 제어를 위해서는 직관적인 사용자 인터페이스가 필요하다. 이 논문에서는 다수개의 Myo로 UAV를 제어하는 방법을 제안한다. 이를 위해서 기 개발된 지상관계시스템을 통해 Myo로 UAV를 제어하는 방법을 소개한다. 체감형 인터페이스로 UAV를 제어함으로써 직관적인 제어가 가능하다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2005년도 ICCAS
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• pp.1008-1013
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• 2005

In this paper, position tracking control of an autonomous helicopter is presented. Velocity is controlled by using an optimal state controller LQR. A position control loop is added to form a PD controller. To minimize a position tracking error, neural network is introduced. The reference compensation technique as a neural network control structure is used, and a position tracking error of an autonomous helicopter is compensated by neural network installed in the remotely located ground station. Considering time delays between an autonomous helicopter and the ground station, simulation studies have been conducted. Simulation results show that the LQR with neural network compensation performs better than that of the LQR itself.

• Journal of Astronomy and Space Sciences
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• 제27권3호
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• pp.195-204
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• 2010

The optimal Earth-Moon transfer trajectory considering spacecraft's visibility from the Daejeon ground station visibility at both the trans lunar injection (TLI) and lunar orbit insertion (LOI) maneuvers is designed. Both the TLI and LOI maneuvers are assumed to be impulsive thrust. As the successful execution of the TLI and LOI maneuvers are crucial factors among the various lunar mission parameters, it is necessary to design an optimal lunar transfer trajectory which guarantees the visibility from a specified ground station while executing these maneuvers. The optimal Earth-Moon transfer trajectory is simulated by modifying the Korean Lunar Mission Design Software using Impulsive high Thrust Engine (KLMDS-ITE) which is developed in previous studies. Four different mission scenarios are established and simulated to analyze the effects of the spacecraft's visibility considerations at the TLI and LOI maneuvers. As a result, it is found that the optimal Earth-Moon transfer trajectory, guaranteeing the spacecraft's visibility from Daejeon ground station at both the TLI and LOI maneuvers, can be designed with slight changes in total amount of delta-Vs. About 1% difference is observed with the optimal trajectory when none of the visibility condition is guaranteed, and about 0.04% with the visibility condition is only guaranteed at the time of TLI maneuver. The spacecraft's mass which can delivered to the Moon, when both visibility conditions are secured is shown to be about 534 kg with assumptions of KSLV-2's on-orbit mass about 2.6 tons. To minimize total mission delta-Vs, it is strongly recommended that visibility conditions at both the TLI and LOI maneuvers should be simultaneously implemented to the trajectory optimization algorithm.

• 한국위성정보통신학회논문지
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• 제1권2호
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• pp.45-50
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• 2006

위성체와 지상국은 위성 운영 전에 접속이 가능한지 여부를 시험한다. 이러한 호환성 시험은 위성체와 지상국의 요구상항이 각각 검증된 후에 위성체와 지상국을 연결하여 시험한다. RF 호환성 시험의 내용은 접속 제어문서에 기술된 요구사항이 잘 개발되었는지 확인하는 것이다. 위성의 초기 운용 기간이나 일시적인 비상 운용상황에서는 항우연 지상국은 해외의 지상국을 이용한다. 해외 지상국은 국내의 특정한 위성 개발 프로그램 하에서 개발된 것이 아니기 때문에 시스템 차원에서 해외 지상국이 접속 요구사항을 만족하는지 검증해야 한다. RF 이동장비를 이용하면 항우연 지상국의 지원없이 해외 지상국에서 직접 접속 요구조건과 통신 내용을 검증할 수 있다. RF 이동장비를 이용한 RF 호환성 시험이 해외지상국과 항우연의 지상국에서 수행되었다. RF 호환성 시험의 항목은 다를 해외 지상국에서 이용할 수 있도록 표준화되었으며 발사 및 초기운용 기간의 운용 개념에 맞추었다. 시험 항목은 RF 특성, 프로토콜, 원격명령 및 원격측정 루프 시험, 지상국 접속 시험 등이다.