• Journal of the Korea Institute of Military Science and Technology
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• v.24 no.6
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• pp.577-590
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• 2021

In this paper, we theoretically analyzed the self-alignment/navigation performance in the accelerometer resonance state generated by dither motion of ring laser gyroscope in LINS and verified it through simulation. As a result of analysis, it is confirmed that the amplitude of the accelerometer measurement amplified in the accelerometer resonance state is decreased in the process of sampling per the navigation calculation period and that frequency is changed by the aliasing effect too. It was also analysed that the attitude error in self-alignment is determined by the amplitude/frequency of the accelerometer measurement, the gain of the self-alignment loop, and the velocity and position error in the navigation is determined by the amplitude/frequency/phase error of the accelerometer measurement. This analysis and simulation results show that the self-alignment and navigation performance is not be degraded only when the amplification factor of the accelerometer measurement in the accelerometer resonance state is 3 or less

• Korean Journal of Optics and Photonics
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• v.14 no.6
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• pp.649-656
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• 2003

In this paper we confirm the relation between the phase and phase error of the beat signal at the lock-in region of the dither type ring laser gyroscope by numerical calculation. We also study the requirement of the dither noise of an amplitude modulation type for statistical zero averaging of the beat signal phase error, without accumulation. As a result, we find that the dither noise requires the increase and decrease gradients of the dither amplitude, and those gradients should be combined with similar white noise. The slope of the gradient and maximum/minimum amplitude must be changed randomly. We confirm the error accumulation characteristic related to the dither noise by comparison of the two outputs during temperature change, by operating the two kinds dither noise, one is satisfied with the requirement and the other is not.

• Proceedings of the Optical Society of Korea Conference
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• 2002.11a
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• pp.168-169
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• 2002

• Journal of the Korea Institute of Military Science and Technology
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• v.10 no.1
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• pp.107-115
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• 2007

In this paper we confirm the disappearance of dynamic lock-in simply by increasing the dither noise magnitude of the ring laser gyroscope by numerical and experimental method. After that, we numerically study the relation between the dither noise forms and scale factor non-linearities by comparing those of the two case outputs which are individually generated by operating with the two types of dither noise forms. The first one is the simple form composed of consecutive alternations of the random increasing and decreasing parts but maximum and minimum dither envelopes are scarcely changeable. And the second one is similar to the first one but maximum and minimum dither envelopes are randomly changable. As a result, we find that the scale factor non-linearity could be improved by the second one. And we confirm those results by experimental measurements.

• Journal of the Korea Institute of Military Science and Technology
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• v.21 no.6
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• pp.731-743
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• 2018

In this paper, a study result to decide the accuracy specifications of inertial sensors satisfying the performance requirements of SINS(ship's inertial navigation system) is proposed. To do this, the performance specifications of overseas SINS is surveyed and the detailed error analysis of SINS at stationary condition is performed. Also, a new performance index to indicate the performance of SINS is derived. Modelling and simulation results show that the accuracy specifications of inertial sensors to meet the performance requirements of SIGMA40XP, a typical overseas SINS, can be determined through the newly derived performance index in this paper.

• 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.

• Proceedings of the Optical Society of Korea Conference
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• 2000.08a
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• pp.62-63
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• 2000

다양한 분야의 요구에 따라 반사율이 99.995% 이상인 고반사 저손실 반사경의 제작이 가능해 지면서 반사경의 산란, 투과, 흡수 및 손실 등을 측정하는 여러 측정 방법들도 더불어 연구되어 왔다. 적용 분야에 따라 사용될 반사경의 특성이 결정되는데 그 중 중력파 측정 장치$^{(1)}$ , 광자 감쇠 분광기$^{(2)}$ 등의 분야에서는 투과, 산란 및 흡수가 모두 작은 저손실 반사경을 요구한다. 한편 링 레이저 자이로스코프의 경우 반사경의 산란이 곧 lock-in을 결정하여 성능을 제한하는 중요한 변수가 된다. 따라서 이 응용의 경우 반사경의 산란을 정확히 측정하는 일은 중요하며 위치에 따른 산란분포 정보를 알면 링 레이저 자이로스코프의 성능 예측과 개선이 더욱 쉬워진다. 산란을 측정하는 직접적인 방법에는 ARS(angle resolved scattering)과 TIS(total integrated scattering)이 있는데, 본 연구에서는 TIS 측정 장비를 반사경의 위치에 따른 산란분포까지 측정할 수 있도록 mapping 기능을 첨가하고 이온빔 스퍼터링에 의해 제작된 저산란 반사경을 측정하기 위해 높은 분해능을 갖도록 구성하였다. 반사경의 응용분야의 필요에 의해 45$^{\circ}$ 산란을 측정하였다. (중략)

• Korean Journal of Optics and Photonics
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• v.8 no.6
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• pp.456-460
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• 1997

Several methods of aligning ring type cavities have been investigated for long time. The measurement of cavity transmission spectrum control is somewhat effective due to aligning cavity with measuring cavity loss at the same time. In this research, four mirrors are aligned and attached by the measurement of pulse width of the transmitted light. The intracavity loss is optimized to about 0.98%, giving the calculated total reflection coefficient of about 99.02%.

• Journal of the Korean Society of Manufacturing Technology Engineers
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• v.22 no.1
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• pp.107-111
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• 2013

The gyroscopes have been used as a suitable inertial instrument for the navigation guidance and attitude controls. The accuracy as very sensitive sensor is limited by the lock-in region (dead band) due to the frequency coupling between two counter-propagating waves at low rotation rates. This frequency coupling gives no phase difference, and an angular increment is not detected. This problem can be overcome by mechanically dithering the gyroscope. This paper presents the design method of mechanical dither by the theoretical considerations and the verification of the theoretical equations through FEM applications. As a result, comparing to the past result, the maximum prediction error of resonant frequency was within 3 percent and peak dither rate was within 5 percent. It was found that the theoretical equations can be feasible for the mechanical performance of dither.

• Journal of the Korea Institute of Military Science and Technology
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• v.18 no.2
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• pp.109-114
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• 2015

A method to compensate a bias hysteresis error of the ring laser gyro using the rate of temperature is proposed in this paper. Until now, we generally have measured and compensated the error of gyro and accelerometer using the temperature. However, we utilize the measured values of the temperature dependent error elements on the temperature rate in navigation system level. We show through experiments that the proposed method can improve the navigation performance and be very effective.