Aerospace Engineering and Technology (항공우주기술)

Korea Aerospace Research Institute (한국항공우주연구원)
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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

  • 김의찬 (한국항공우주연구원 위성전자팀) ;
  • 양군호 (한국항공우주연구원 통해기체계팀)
  • Received : 2010.01.04
  • Accepted : 2010.10.01
  • Published : 2010.11.01
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Abstract

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.

Keywords

References

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