• 전기학회논문지
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• 제57권2호
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• pp.256-260
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• 2008

The Ring Laser Gyro makes use of the Sagnac effect within a resonant ring cavity of A He-Ne laser and has more accuracy than the other Gyros. The Low Earth Orbit satellite for observatory use require the high accuracy Gyro to control and determine the altitude because of the need of payload pointing accuracy. In this paper, The theory of the Path Length Control is explained. The electrical design of Path Length Controller is described. The Design for Path Length Controller is composed of the demodulator, Integrator, Phase shifter, High Voltage Amplifier. We apply the circuit to 28cm square ring laser gyro and get the test results.

• 한국광학회지
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• 제15권1호
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• pp.68-73
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• 2004

간섭계를 이용한 링레이저 자이로의 플렉셔 각도 측정기법이 연구되었다. Dummy mass를 추가하여 중력가속도 이상의 고가속도 환경을 구현하였으며, 이에 따른 피에조 간섭무늬의 변화로부터 자이로 입력축의 단위 중력가속도에 대한 플렉셔 각도 변화를 조사하였다. 링레이저 자이로가 가지는 플렉셔 각도 변화계수는 2.37 arcsec/g로,플렉셔 측정 반복도 오차는 0.07arcsec/g정도로 측정되었다. 플렉셔 각도를 감소시켰을 때, 링레이저 자이로 관성항법장치의 플렉셔 오차가 뚜렷이 개선됨을 확인하였다.

• 전기학회논문지
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• 제57권3호
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• pp.403-408
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• 2008

The gyroscope is the sensor for detecting the rotation in inertial reference frame and constitute the navigation system together an accelerometer. As the inertial reference equipment for attitude determination and control in the satellite, the mechanical gyroscope has been used but it bring the disturbance for mass unbalance so the disturbance give a bad influence to the observation satellite mission because the mechanical gyroscope has the rotation parts. During the launch. The mechanical gyroscope is weak in vibration, shock and has the defect of narrow operating temperature range so it need the special design in integration. Recently the low orbit observation satellite for seeking the high pointing accuracy of image camera payload accept the FOG(Fiber Optic Gyro) or RLG(Ring Laser Gyro) for the attitude determination and control. The Ring Laser Gyro makes use of the Sanac effect within a resonant ring cavity of a He-Ne laser and has more accuracy than the other gyros. It need the 1000V DC to create the He-Ne plasma in discharge tube. In this paper, the design process of the High Voltage Power Supply for RLG(Ring Laser Gyroscope) is described. The specification for High Voltage Power Supply (HVPS) is proposed. Also, The analysis of flyback converter topology is explained. The Design for the HVPS is composed of the inverter circuit, feedback control circuit, high frequency switching transformer design and voltage doubler circuit.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.56.2-56
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• 2001

For the improvement of minimum sensing angular velocity of ring laser gyro, the influence of a low-scattering mirror application to laser resonator was investigated. Super polishing technique was employed for the fine mirror substrates of less than 1-${\AA}$-rms roughness. Mirror coating using ion-beam sputtering coating machine produced low-scattering mirror less than 30-ppm scattering. As a result of the mirror application to ring laser, the minimum sensing angular velocity of the gyro was improved down to about 0.1 deg/sec.

• 항공우주기술
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• 제9권2호
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• pp.31-35
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• 2010

The Ring Laser Gyroscope makes use of the Sagnac effect within a resonant ring cavity of a He-Ne laser and has more accuracy than the other gyros. The space launch vehicle use require the high accuracy Gyro to control and determine the altitude to deliver the satellite in the space. In this paper, The theory of the Path Length Control is explained. The electrical design of Path Length Controller is described. The Design for Path Length Controller is composed of the demodulator, integrator, phase shifter, high voltage amplifier. We apply the circuit to 28cm square ring laser gyro and get the test results.

• 대한전자공학회:학술대회논문집
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• 대한전자공학회 2009년도 정보 및 제어 심포지움 논문집
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• pp.341-343
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• 2009

The Ring Laser Gyroscope makes use of the Sagnac effect within a resonant ring cavity of a He-Ne laser and has more accuracy than the other gyros. The Low Earth Orbit satellite for observatory use require the high accuracy Gyro to control and determine the altitude because of the need of payload pointing accuracy. In this paper, The theory of the Path Length Control is explained. The electrical design of Path Length Controller Is described. The Design for Path Length Controller is composed of the demodulator, integrator, phase shifter, high voltage amplifier. We apply the circuit to 28cm square ring laser gyro and get the test results.

• 전기학회논문지
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• 제57권9호
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• pp.1584-1588
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• 2008

The Ring Laser Gyroscope makes use of the Sagnac effect within a resonant ring cavity of a He-Ne laser and has more accuracy than the other gyros. The Low Earth Orbit satellite for observatory use require the high accuracy Gyro to control and determine the altitude because of the need of payload pointing accuracy. In this paper, The theory of the Path Length Control is explained. The electrical design of Path Length Controller is described. The Design for Path Length Controller is composed of the demodulator, integrator, phase shifter, high voltage amplifier. We apply the circuit to 28cm square ring laser gyro and get the test results.

• 한국항공우주학회지
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• 제33권8호
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• pp.65-74
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• 2005

공진기 진동형 링레이저 자이로가 외부에서 입력되는 각도변화만을 검출하여 출력하기 위해서는 링레이저 출력으로부터 공진기의 각진동 운동에 의한 출력을 제거하는 방법이 필요하다. 본 논문에서는 공진기 진동형 링레이저 자이로에서 공진기의 각진동을 검출하는 각속도 센서 출력을 V-F 변환하여 링레이저 출력을 보상하는 dither-stripping에 대하여 논의하였다. 우리는 V-F 신호의 offset을 제거하기 위하여 V-F 신호의 미분값을 취하고 또한 미분값을 취함으로서 변화되는 위상을 보상하기 위하여 아날로그 적분기로 위상을 보정하는 방법과 링레이저 신호 또는 V-F 신호의 검출 시점을 지연시키는 방법을 개발하였다. 그리고 링레이저 출력과 V-F 신호 사이의 환산을 위하여 분산을 이용하여 이득을 산출하는 방법을 개발하였다. 우리는 이와 같은 방법을 적용하고, dither trapping 방법과 비교하는 실험을 통하여 효과를 분석하였다.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2008년도 제39회 하계학술대회
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• pp.1488-1490
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• 2008

The gyroscope is the sensor for detecting the rotation in inertial reference frame and constitute the navigation system together an accelerometer. As the inertial reference equipment for attitude determination and control in the satellite, the mechanical gyroscope has been used but it bring the disturbance for mass unbalance so the disturbance give a bad influence to the observation satellite mission because the mechanical gyroscope has the rotation parts. During the launch, The mechanical gyroscope is weak in vibration, shock and has the defect of narrow operating temperature range so it need the special design in integration. Recently the low orbit observation satellite for seeking the high pointing accuracy of image camera payload accept the FOG(Fiber Optic Gyro) or RLG(Ring Laser Gyro) for the attitude determination and control. The Ring Laser Gyro makes use of the Sanac effect within a resonant ring cavity of a He-Ne laser and has more accuracy than the other gyros. It need the 1000V DC to create the He-Ne plasma in discharge tube. In this paper, the design process of the High Voltage Power Supply for RLG(Ring Laser Gyroscope) is described. The specification for High Voltage Power Supply(HVPS) is proposed. Also, The analysis of flyback converter topology is explained. The Design for the HVPS is composed of the inverter circuit, feedback control circuit, high frequency switching transformer design and voltage doubler circuit.

• 한국군사과학기술학회지
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• 제22권2호
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• pp.189-196
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• 2019

The inertial sensor errors in SDINS(Strapdown Inertial Navigation System) can be compensated by rotating the inertial measurement unit and it is called RINS(Rotational Inertial Navigation System). It is assumed that the error of the inertial sensor in RINS is a static bias. However, the error of the inertial sensor actually developed and produced is not a static bias due to the change of the temperature applied to the sensor and the influence of the earth's gravity acceleration. In this paper, we propose a six-position gyro bias calibration method to evaluate the gyro bias required for RINS and present the test results of applying it to a ring laser gyro inertial navigation system under development.