• 제어로봇시스템학회:학술대회논문집
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• 1996.10b
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• pp.856-859
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• 1996

In this paper, a coarse alignment algorithm for strapdown inertial navigation system is proposed and evaluated analytically. The algorithm computes roll and pitch angles of the vehicle using accelerometer outputs, and then determines yaw angle with gyro outputs. It is referred, as two-step coarse alignment in this work. With the geometric relation between sensor outputs and roll, pitch and yaw angles, the algorithm error is analytically derived and compared with the previous coarse alignment algorithm introduced by Britting. The results show that the proposed two-step coarse alignment algorithm has better performance for pitch angle computation.

• Journal of Institute of Control, Robotics and Systems
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• v.4 no.5
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• pp.674-679
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• 1998

In this paper, a new coarse alignment algorithm is proposed for roughly determining the initial attitude of the vehicle. The algorithm, referred as two-step coarse alignment algorithm, computes roll and pitch angle of the vehicle using accelerometer outputs, and then determines yaw angle with gyro outputs. With the geometric relation between sensor outputs and attitude angles, the algorithm error is analytically derived and compared with the previous coarse alignment algorithm that computes a transformation matrix using accelerometer md gyro outputs simultaneously. The simulation is also performed by varying the sensor errors. The results show that the proposed two-step coarse alignment algorithm has better performance for east tilt angle.

• Journal of Institute of Control, Robotics and Systems
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• v.8 no.6
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• pp.524-532
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• 2002

This paper presents a new in-flight alignment method for an SDINS under large initial heading error. To handle large heading error, a new attitude error model is introduced. The attitude errors are divided into heading error and leveling errors using a newly defined horizontal frame. Some navigation error dynamic models are derived from the attitude error model for indirect feedback filtering of the in-flight alignment system. A Kalman filter with Position measurement is designed to estimate navigation errors as the indirect feedback filter Simulation results show that the proposed in-flight alignment method reduces the heading error very quickly from more than 40deg to about 5deg so as to apply a refined navigation filter. The total alignment process including leveling mode and navigation mode in addition to the proposed one allows large initial values not only in heading error but also in leveling errors.

• The Journal of Korean Association of Computer Education
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• v.6 no.1
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• pp.1-8
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• 2003

We introduce a efficient vertical mining algorithm that reduces searching complexity for frequent k-itemsets significantly. This method includes sorting items by their LSI(Least Support Itemsets) similarity and then searching frequent itemsets in tree-based manner. The search tree structure provides several useful heuristics and therefore, reduces search space significantly at early stages. Experimental results on various data sets shows that the proposed algorithm improves searching performance compared to other algorithms, especially for a database having long pattern.

• 한국정보통신설비학회:학술대회논문집
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• 2006.08a
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• pp.235-240
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• 2006

In order to enhance receive sensitivity in noisy environment, the previous initial synchronization method of GPS receiver for reference stations adopts not only the coherent integration method but also the non-coherent integration method. However, the previous GPS initial synchronization method causes the non-coherent integration loss, which is a dominant factor among the signal acquisition losses in noisy environment. And the non-coherent integration loss increases with the strength of noise signal. In this pa-per, a GPS initial synchronization method is proposed to enhance receive sensitivity of GPS receiver for reference stations in noisy environment. This paper presents that the proposed GPS initial synchronization method suppresses the non-coherent integration loss. Furthermore, with regard to the mean acquisition time, it is shown that the number of the search cells of the proposed GPS initial synchronization method is much fewer than that of the previous GPS initial synchronization method.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• v.2
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• pp.451-454
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• 2006

본 논문에서는 헬기의 인공 시계 시스템용 DGPS/INS 통합 항법 플랫폼을 설계하였다. DGPS/INS 통합 항법 플랫폼 하드웨어는 PowerPC CPU와 Flash ROM과 DDR SDRAM를 이용하여 설계하였다. DGPS 수신기와 IMU와의 연결을 위한 외부 인터페이스부는 직렬 통신을 사용하는 DGPS수신기와 IMU는 모두 사용할 수 있도록 하기 위하여 직렬 통신 방식인 UART 컨트롤러와 SDLC 컨트롤러를 사용하여 설계하였다. 실시간 운영체제를 기반으로 하는 플랫폼의 소프트웨어는 초기 정렬, 자세 계산, 속도 계산, 위치 계산, 통합 필터, 명령 처리 각각에 대하여 태스크로 구성하고 세마포어를 이용하여 태스크간의 동기가 이루어지도록 설계하였다. 통합 항법 플랫폼의 성능 평가를 위하여 차량 실험을 수행하였으며 상용 항법 시스템의 결과와 비교를 하였다.

• Proceedings of the KIEE Conference
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• 2007.07a
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• pp.1595-1596
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• 2007

광통신에 있어서 광소자와 광섬유 사이의 광결합효율이 중요하다. 광효율을 증가시키기 위하여 파이버 연마 과정이 필요하다. 기존 파이버 연마 장치는 대부분 외국 장비이고 단일모드만 작동되고 대량 생산이 용이하지 않으며 데이터 저장과 긴급상황 발생시 대처가 떨어지는 단점이 있다. 본 연구에서는 이를 보안하기 위하여 PC기반의 본 시스템을 개발하였다. 이 시스템은 여러 종류의 샘플 가공과 코어의 자동 정렬이 가능하며 PD데이터를 자동 저장한다. 또한 연마 거리를 자동 계산하여 연마 필름의 낭비를 줄였다. 정전과 같은 긴급상황 발생시 데이터를 보존하여 다음 연마시 기존 데이터로 초기화가 가능하다.

• Proceedings of the Korean Vacuum Society Conference
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• 2010.02a
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• pp.344-344
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• 2010

그라핀 나노리본은 독특한 전기적 특성으로 인하여 차세대 나노 소자용 신소재로 주목을 받고 있으며 리본의 폭과 가장자리 구조에 따라 여러 가지 다른 특성을 나타낸다고 알려져 있다. 우리는 Scanning Tunneling Microscopy(STM) 실험을 통하여 기울어진 6H-SiC(0001) 면 위에서 그라핀 나노리본의 성장 가능성을 조사하고 성장된 그라핀 나노구조의 가장자리에서 나타나는 구조에 대하여 연구하였다. 그라핀 성장의 초기 단계에서는 리본 형태의 그라핀 나노 구조를 볼 수 있었으나 그라핀 성장 과정을 거치면서 SiC 기판의 잘 정렬된 계단 구조가 망가져서 그라핀 나노리본 배열의 형성에는 한계가 있음을 확인할 수 있었다. 원자 수준의 STM 이미지를 통해서 그라핀 나노 구조의 가장자리에서 큰 육각형 형태의 양자 간섭 무늬를 관찰하였는데 이러한 형태는 흑연 위의 그라핀 나노 조각에 대한 연구에서 관찰된 것과 동일한 것으로 Armchair 형태의 가장자리 구조의 경우에 형성된다고 알려져 있다.[1] 이로부터 SiC(0001) 표면위에 형성된 그라핀 나노 구조의 경우에도 Armchair 형태의 가장자리 구조가 더 안정적임을 알 수 있었다. 이러한 구조의 국소 전자 구조에 대하여 알아보기 위하여 Scanning Tunneling Spectroscopy 측정도 함께 수행하였다.

• Journal of the Korea Institute of Military Science and Technology
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• v.22 no.4
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• pp.467-474
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• 2019

Recently, optical phased array(OPA) based laser detection and ranging(LADAR) has gained great interest to replace the traditional mechanical light detection and ranging technique(LiDAR). In OPA-based LADAR, it is well known that phases of laser pulses traveling through each of channels should be the same to obtain a narrow free-space single beam without noise-like ripples in the far field. However, it is difficult to provide such ideal condition due to the fabrication errors. To tackle this problem, any algorithms should be necessary to compensate the initial random phases of each channel in OPA antenna. In this paper, we propose a hill-climbing based phase calibration algorithm and evaluate the performance of the proposed algorithm.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.11
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• pp.761-767
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• 2019

In the present study, analyses of initial behavior of an air-launched projectile for varying initial conditions are performed by coupling computational fluid dynamics and 6 degrees of freedom calculations. Accuracy of the present numerical methods is validated by comparing the present result with the measured data. Launching safety analyses are carried out for various ejecting conditions by considering weight of the projectile and magnitude of front and rear ejector forces as the major parameters of initial behavior of the projectile. A response surface of the projectile launching safety is obtained in the range of the major parameters. In all the conditions of zero rear ejector force, unsafe launching behavior is observed. As the weight of the projectile decreases, the initial launching behavior becomes more unsafe.