• 제어로봇시스템학회논문지
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• 제6권2호
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• pp.138-145
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• 2000

In this paper an initial alignment algorithm for a strapdown inertial navigation system is implemented using a RISC CPU board. The algorithm computes roll pitch and yaw angles of the direction cosine matrix utilizing measured components of the specific force and earth rate when the navigation system is stationary. The coarse alignment algorithm is performed first and then the fine alignment algorithm containing a 3rd-order gyrocompass loop follows. The experimental set consists of an IMU a CPU board and a monitoring system Experimental results show that the implemented algorithm can be utilized in navigation systems.

• International Journal of Aeronautical and Space Sciences
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• 제11권3호
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• pp.184-192
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• 2010

In this paper, an initial fine alignment algorithm, which is developed for the strap-down inertial navigation systems of satellite launch vehicles, is considered. For fast and accurate alignment, a simple closed-loop estimation algorithm using a proportional-integral controller is introduced. Through computer simulation for the sway condition in the launch pad, it is shown that a simple filter structure can guarantee fast computational speed that is adequate for real-time implementation as well as the required alignment accuracy and robustness. In addition, its implementation results are presented for the Naro-1 flight test.

• 제어로봇시스템학회논문지
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• 제14권6호
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• pp.595-602
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• 2008

In this paper, performance of the initial alignment for INS whose attitude is not leveled is investigated. Observability of the initial alignment filter is analyzed and estimation errors of the estimated state variables are derived. First, the observability is analyzed using the rank test of observability matrix and the normalized error covariance of the Kalman filter based on the 10-state model. In result, it can be seen that the accelerometer biases on horizontal axes are unobservable. Second, the steady-state estimation errors of the state variables are derived using the observability equation. It is verified that the estimates of the state variables have errors due to the unobservable state variables and the non-leveling tilt angles of a vehicle containing the INS. Especially, this paper shows that the larger the tilt angles of the vehicle are, the larger the estimation errors corresponding to the sensor biases are. Finally, it is shown that the performance of the 8-state model excepting the accelerometer biases on horizontal axes is better than that of the 10-state model in the initial alignment by simulation.

• 한국항해항만학회:학술대회논문집
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• 한국항해항만학회 2006년도 International Symposium on GPS/GNSS Vol.1
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• pp.355-359
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• 2006

For the poor observability of azimuth misalignment angle and east gyro drift rate of the traditional initial alignment, a bran-new SINS stationary fast self-alignment approach is proposed. By means of analyzing the characteristic of the strapdown inertial navigation system (SINS) stationary alignment seriously, the new approach takes full advantage of the specific force and angular velocity information given by inertial measurement unit (IMU) instead of the mechanization of SINS. Firstly, coarse alignment algorithm is presented. Secondly, a new fine alignment model for SINS stationary self-alignment is derived, and the observability of the model is analysed. Then, a modified Sage-Husa adaptive Kalman filter is introduced to estimate the misalignment angles. Finally, some computer simulation results illustrate the efficiency of the new approach and its advantages, such as higher alignment accuracy, shorter alignment time, more self-contained and less calculation.

• International Journal of Aeronautical and Space Sciences
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• 제18권3호
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• pp.565-573
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• 2017

This paper presents a multistage in-flight alignment (MIFA) method for a strapdown inertial navigation system (SDINS) suitable for moving vehicles with no initial attitude references. A SDINS mounted on a moving vehicle frequently loses attitude information for many reasons, and it makes solving navigation equations impossible because the true motion is coupled with an undefined vehicle attitude. To determine the attitude in such a situation, MIFA consists of three stages: a coarse horizontal attitude, coarse heading, and fine attitude with adaptive Kalman navigation filter (AKNF) in order. In the coarse horizontal alignment, the pitch and roll are coarsely estimated from the second order damping loop with an input of acceleration differences between the SDINS and GPS. To enhance estimation accuracy, the acceleration is smoothed by a scalar filter to reflect the true dynamics of a vehicle, and the effects of the scalar filter gains are analyzed. Then the coarse heading is determined from the GPS tracking angle and yaw increment of the SDINS. The attitude from these two stages is fed back to the initial values of the AKNF. To reduce the estimated bias errors of inertial sensors, special emphasis is given to the timing synchronization effects for the measurement of AKNF. With various real flight tests using an UH60 helicopter, it is proved that MIFA provides a dramatic position error improvement compared to the conventional gyro compass alignment.

• 한국항해항만학회:학술대회논문집
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• 한국항해항만학회 2006년도 International Symposium on GPS/GNSS Vol.1
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• pp.115-120
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• 2006

This article propose a new idea of developing a hybrid scheme to achieve faster INS alignment with higher accuracy using a novel procedure to estimate the initial attitude angles that combines a Kalman filter and Adaptive Neuro-Fuzzy Inference System architecture. A tactical grade inertial measurement unit was applied to verify the performance of proposed scheme in this study. The preliminary results indicated the outstanding improvements in both time consumption for fine alignment process and accuracy of estimated attitude angles, especially in heading angles. In general, the improvement in terms of time consumption and the accuracy of estimated attitude estimated accuracy reached 80% and 70% respectively during alignment process after compensating the attitude angles estimated by an extended Kalman filter with 15 states using proposed approach. It is worth mentioned that the proposed approach can be implemented in general real time navigation applications.

• Journal of the Optical Society of Korea
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• 제19권6호
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• pp.604-613
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• 2015

An unobstructed off-axis two-mirror system is presented in this paper. First a suitable initial configuration is established based on third-order aberration theory. In order to achieve a wide field of view (FOV) with high image quality , the diffractive mirror is adopted in the two-mirror system to increase the optimization freedom and the aberration relationship between diffractive phase coefficients and Zernike coefficients is derived. Furthermore, a complete comparison design example with a focal length of 1200 mm, F-number of 12, and FOV of 40° × 2° is given to verify the aberration correction ability of the diffractive mirror. The system average wavefront error is 0.007 λ (λ=0.6328 μm) developed from 0.061 λ when the system didn’t adopt the diffractive mirror. In this system the phase modulation function of the diffractive mirror is established as an even function of x, so we could obtain a symmetrical imaging quality about the tangential plane, and the symmetric aberration performance also brings considerable convenience to alignment and testing for the system.

• Journal of Astronomy and Space Sciences
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• 제19권4호
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• pp.351-366
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• 2002

본 연구에서는 저가의 INS와 GPS 정보를 합성하여 고기동 환경에서 항체의 위치와 자세정보를 연속적으로 제공할 수 있는 약결합 방식의 통합 알고리즘을 구현하였고, 4S-Van에 장착된 이미지 센서의 위치와 자세결정 방법에 사용하였다. (D)GPS/INS 통합을 실시하기 전 IMU의 초기 정렬과정에서 방위각은 두 대의 GPS를 통해 결정하였으며 칼만 필터를 이용한 정밀정렬을 수행하였다. 통합 알고리즘의 성능평가를 위해 차량 테스트와 시뮬레이션 테스트를 병행하였다. 통합 결과 차량 시험을 기준으로 나타난 위치 오차는 직선도로에서 l0cm 내외의 정확도를 보이며 자세오차의 경우 시뮬레이션을 기준으로 롤각은 $0^{\circ}.01$, 피치각은 $0^{\circ}.03$, 요각은 $0^{\circ}.1$ 내외의 정확도를 보였다. 구현된 (D)GPS/INS 알고리즘은 기하보정 방법을 통해 이미지센서의 위치와 자세정보 제공자로서 활용될 수 있다. 따라서 4S-Van에 장착된 이미지 센서의 영상획득 시각에 대한 기하학적인 정보를 통해 지상의 건물이나 도로 시설물 등에 대한 3차원 공간 자료 구축이 가능하다고 보며, 구축된 정보를 통해 기존의 수치지도 갱신, 도로 시설물 관리, 비디오 GIS 데이터 베이스 구축 등에 대한 공간 자료 연계 및 응용에 활용할 계획이다.

• 한국광학회지
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• 제13권5호
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• pp.384-389
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• 2002

본 논문은 DWDM 응용을 위한 새로운 개념의 파장안정화 모듈을 제안한다. 일반적으로 내장형/외장형 파장안정화기에서는 LD의 파워를 모니터링 하는 모니터 PD 이외에 파장을 모니터링하는 하나의 에탈론 PD가 사용된다. 50 GHz응용에서 에탈론의 각도를 미세 조정하는 방법이 일반적이다. 그러나, 에탈론의 미세 각도 튜닝으로 인한 파장안정화기 성능에 미치는 영향은 대단히 크며 미세 각도로 정렬하는 공정은 매우 어렵다. 에탈론 PD 배열 블록을 사용함으로써 파장안정화 모듈의 기계적인 에탈론 정렬 오차를 낮출 수 있으며 미세 파장 조정이 가능하다. 파장안정화 모듈의 에탈론 각도 조정에 따른 FSR과 최대 투과 파장의 위치 변화 정도를 계산하였으며 본 실험에 사용된 파장안정화 모듈의 최적화된 초기 에탈론 회전 각도를 보고한다.