• 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.

• 한국군사과학기술학회지
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• 제12권5호
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• pp.622-635
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• 2009

Laser Inertial Navigation System(LINS) consists of Ring Laser Gyroscopes(RLG) and accelerometers. RLG has a lock-in region in which there is zero output for input angular rates less than about 0.1deg/sec. The lock-in region is generated by the imperfect mirrors in RLG. To avoid the lock-in region, a sinusoidal motion called dither motion is applied on RLG. Therefore this dither motion is measured by RLG/accelerometer even if at a stop state. In this situation, the performance on the initial alignment of LINS can be degraded. In this paper, we analyze the performance on the initial alignment of LINS theoretically and experimentally. Analysis results include how dither motion, the pre-filter and the corner frequency in alignment loop affects the performance on the initial alignment of LINS.

• 한국군사과학기술학회지
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• 제17권4호
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• pp.537-543
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• 2014

RLG(Ring Laser Gyroscope) is a main device of LINS(Laser Inertial Navigation System). RLG has the lock-in region in which there is no output signal. To alleviate the lock-in problem, a mechanical oscillation, the dither motion, is applied on RLG. A LPF(Low Pass Filter) is usually used on the output of RLG and accelerometer to remove the noise that is made by the dither motion. When the LINS is induced the disturbance during the initial alignment, it takes more time on alignment due to the use of the LPF and a fixed gain controller. In this paper, an initial alignment using UKF(Unscented Kalman Filter) is designed and analysed. Analysis include comparison between conventional initial alignment loop using fixed gain type controller and proposed initial alignment using UKF. Moreover, Disturbance inducing test results are demonstrated.

• 한국항공우주학회지
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• 제46권11호
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• pp.921-933
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• 2018

관성항법장치 순수항법 성능을 개선하는 방법으로 관성센서 오차가 상호 상쇄되도록 관성센서뭉치를 회전시켜 항법 성능을 개선하는 방법이 있으며 이러한 원리로 동작하는 항법장치를 회전형 관성항법장치라 한다. 관성센서 오차에 의한 회전형 관성항법장치의 정확한 항법 성능 분석을 위해서는 이에 대한 이론적 오차해석이 요구되나 기존의 많은 연구에서는 지구회전 각속도 및 중력 가속도에 의한 영향을 무시하고 오차해석을 수행하여 회전형 관성항법장치의 정확한 항법 성능 분석이 수행되지 않았다. 본 논문에서는 링레이저 자이로 기반 회전형 관성항법장치의 정확한 항법 성능 분석을 위하여 지구회전 각속도 및 중력 가속도 항을 포함한 이론적인 오차해석을 수행하고 이를 기반으로 회전형 관성항법장치의 항법 성능 분석 결과를 제시하였다.

• 한국군사과학기술학회지
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• 제24권6호
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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

• 제어로봇시스템학회논문지
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• 제17권11호
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• pp.1106-1116
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• 2011

LINS (Laser Inertial Navigation System) consists of RLG (Ring Laser Gyroscopes)/accelerometers and provides real-time navigation information to the target system. Therefore it is very important to make a decision in the real time whether LINS is in the normal operation or not. That is called a fault detection method. In this paper, we propose the fault detection method of LINS based on the overlapping model. We also show that the fault detection probability is increased through overlapping the hardware model and the software model. It is verified through the long-term operation and RAM (Reliability Availability Maintainability) analysis of LINS that the fault detection method proposed in this paper is able to detect about 97% of probable system failures.

• KSII Transactions on Internet and Information Systems (TIIS)
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• 제17권11호
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• pp.2945-2965
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• 2023

The laser inertial measurement unit is a precision device widely used in rocket navigation system and other equipment, and its quality is directly related to navigation accuracy. In the quality evaluation of laser inertial measurement unit, there is inevitably uncertainty in the index input information. First, the input numerical information is in interval form. Second, the index input grade and the quality evaluation result grade are given according to different national standards. So, it is a key step to transform the interval information input by the index into the data form consistent with the evaluation result grade. In the case of uncertain input, this paper puts forward a method based on probability distribution to solve the problem of asymmetry between the reference grade given by the index and the evaluation result grade when evaluating the quality of laser inertial measurement unit. By mapping the numerical relationship between the designated reference level and the evaluation reference level of the index information under different distributions, the index evidence symmetrical with the evaluation reference level is given. After the uncertain input information is transformed into evidence of interval degree distribution by this method, the information fusion of interval degree distribution evidence is carried out by interval evidential reasoning algorithm, and the evaluation result is obtained by projection covariance matrix adaptive evolution strategy optimization. Taking a five-meter redundant laser inertial measurement unit as an example, the applicability and effectiveness of this method are verified.

• 한국군사과학기술학회지
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• 제21권6호
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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.

• 제어로봇시스템학회논문지
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• 제16권7호
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• pp.617-624
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• 2010

This article describes the system architecture of KUVE (KIST Unmanned Vehicle Electric) and unmanned autonomous navigation of it in KIST. KUVE, which is an electric light-duty vehicle, is equipped with two laser range finders, a vision camera, a differential GPS system, an inertial measurement unit, odometers, and control computers for autonomous navigation. KUVE estimates and tracks the boundary of road such as curb and line using a laser range finder and a vision camera. It follows predetermined trajectory if there is no detectable boundary of road using the DGPS, IMU, and odometers. KUVE has over 80% of success rate of autonomous navigation in KIST.

• 한국항공우주학회지
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• 제42권1호
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• pp.82-89
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• 2014

본 논문에서는 공진기 각진동에 의한 출력을 제거하기 위하여 복조방법을 사용하는 링레이저 자이로의 시간 양자화 오차를 감소시키기 위한 방법을 논의하였다. 링레이저 자이로에는 맥놀이 주파수를 검출하는 과정에서 발생하는 각도 양자화오차와 lock-in 현상을 해결하기 위하여 변조한 각진동을 출력으로부터 복조하는 과정에서 발생하는 시간 양자화오차가 있다. 시간 양자화 오차는 링레이저 자이로의 샘플링 주기가 자이로 각진동 주기에 동기된 복조방법을 사용하기 때문에 발생한다. 일반적으로 자이로 각진동 주기는 항법계산 주기에 비하여 길기 때문에, 탑재체의 자세를 빠른 속도로 업데이트 해야만 하는 고기동 환경에서는 시간양자화 오차에 의한 항법오차가 발생된다. 본 논문에서는 이러한 샘플링 시간 양자화오차를 줄이기 위하여 이중 복조방법을 제안하고, 시뮬레이션을 통하여 동적환경에서의 오차 감소현상을 확인하였다.