• Title/Summary/Keyword: Ring Laser Gyro

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The Design of Path Length Controller in Ring Laser Gyroscope for Attitude Control in the LEO satellite (저궤도 위성 자세제어를 위한 자이로의 광경로 제어기 설계)

  • Kim, Eui-Chan;Lee, Heung-Ho
    • The Transactions of The Korean Institute of Electrical Engineers
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    • v.57 no.2
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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.

Study on flexure angle measurement of ring laser gryo and the improvement of flexure error (링레이저 자이로의 플렉셔 각도측정과 플렉셔 오차개선 연구)

  • 조민식;김광진;김정주
    • Korean Journal of Optics and Photonics
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    • v.15 no.1
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    • pp.68-73
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    • 2004
  • Flexure measurement of ring laser gyro was investigated by using an interferometer. A two-beam interferometer of Fiezo-fringe pattern obtained the flexure angle in 1-gravity acceleration and the higher acceleration environments. These environments were made with the addition of dummy mass to the ring laser gyro axis. The flexure angle change for 1-gravity acceleration change was measured as 2.37 arcsec/g with low repeatability error of 0.01 arcsec/g. The laser navigation system consisting of 3 flexure-reduced ring laser gyros showed the improvement of flexure error.

The Gyro High Voltage Power Supply Design for Attitude Control in the Satellite (저궤도 위성 자세제어용 자이로 고전압 발생기 설계)

  • Kim, Eui-Chan;Lee, Heung-Ho
    • The Transactions of The Korean Institute of Electrical Engineers
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    • v.57 no.3
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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.

Minimum Sensing Angular Velocity Improvement of Ring Laser Gyro Using a Low-Scattering Mirror

  • Jo, Min-Sik;Shim, Kyu-Min;Kim, Hoe-Young;Cho, Hyun-Ju;Jun, Gab-Song;Son, Seong-Hyun
    • 제어로봇시스템학회:학술대회논문집
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    • 2001.10a
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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.

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The Design of Path Length Controller in Ring Laser Gyroscope for Attitude Control in the space launch vehicle (우주발사체 자세제어용 링 레이저 자이로 피에조 구동기 설계)

  • Kim, Eui-Chan;Yang, Koon-Ho
    • Aerospace Engineering and Technology
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    • v.9 no.2
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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.

The Design of Path Length Controller in Ring Laser Gyroscope for Attitude Control in the LEO satellite (위성 자세제어 자이로 센서 피에조 구동기 설계)

  • Kim, Eui-Chan
    • Proceedings of the IEEK Conference
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    • 2009.05a
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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.

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The Design of Path Length Controller in Ring Laser Gyroscope for Attitude Control in the LEO satellite (저궤도 위성 자세제어 센서 RLG 피에조 구동기 설계)

  • Kim, Eui-Chan;Lee, Heung-Ho
    • The Transactions of The Korean Institute of Electrical Engineers
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    • v.57 no.9
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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.

Dither-stripping with the differential of dither rate signal for a ring laser gyroscope (링레이저 자이로의 각진동 센서신호 미분에 의한 dither-stripping)

  • Shim, Kyu-Min;Chung, Tae-Ho;Lim, Hoo-Jang
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.33 no.8
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    • pp.65-74
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    • 2005
  • It is required for getting the ring laser gyro output purely related to the input rotation to eliminate the output of the modulated angular vibration from the ring laser signal. In this paper we discuss the dither stripping methods of compensating the ring laser signal by converting the rate signal of dither detector from voltage to frequency for a dither type ring laser gyro. We discuss the differential methods for getting rid of the offset of the V-F signal. And we develope the methods of compensating the phase differences between the ring laser signals and the V-F differential signals by using analog integrator and digital time delays. And also, we develope the gain calculation method by comparing the standard deviations of the ring laser signals with V-F differential signals. We implemented these methods and analyzed the effectiveness of these methods by comparing the dither trapping methods.

The RLG's Power Supply Design for Attitude Control in the Satellite (저궤도 위성 자세제어용 센서 RLG 전원 공급기 설계)

  • Kim, Eui-Chan;Lee, Heung-Ho
    • Proceedings of the KIEE Conference
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    • 2008.07a
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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.

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The Six-Position Calibration Technique of Gyro Bias for Rotational Inertial Navigation System Based on Ring Laser Gyroscope (링 레이저 자이로 기반 회전형 관성항법장치를 위한 6-자세 자이로 바이어스 교정 방법)

  • Yu, Haesung;Kim, Cheon-Joong;Lee, Inseop;Oh, Ju-Hyun;Sung, Chang-Ky;Lee, Sangjeong
    • Journal of the Korea Institute of Military Science and Technology
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    • v.22 no.2
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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.