• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.2
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• pp.171-177
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• 2012

In this paper, we proposed a algorithm and an operation boundary for fault detection of a onboard GNSS receiver. After aircraft exchange corrections computed by an aircraft receiver, a faulty aircraft receiver is detected by checking consistency of correction. For this purpose, PRC residual is used as the test statistic for fault detection of the onboard GNSS receiver. And operation boundaries are set by using DGPS position error increase with respect to the distance from a reference station. If the fault detection is performed by using aircraft only in operation boundary, the more accurate fault detection can be possible.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.4
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• pp.284-290
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• 2013

The authors propose a nonlinear unknown input observer to estimate the angular speed of a satellite and to detect faults of reaction wheels. Input values are necessary to estimate the angular speed. Therefore, estimation errors are inevitable if faults occur in actuators or reaction wheels. Unknown input observers are useful to estimate the states of a system without being affected by unknown faults. The authors have designed a nonlinear unknown input observer by using the SDRE method and verified the proposed observer via numerical simulations. In spite of various and simultaneous faults, we have estimated the states and detected faults exactly by the proposed nonlinear unknown input observer.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.21-28
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• 2007

The goal of this paper is to represent a technique of fault detection for the control surface as a base research of the fault tolerant control system for safety improvement of UAV. The real-time system identification based on the recursive Fourier Transform was implemented for the fault detection of the control surface and verified through the HILS and flight test. The failures of the control surface are detected by comparing the control derivatives in fault condition with the normal condition. As a result from the flight test, we have confirmed that the control derivatives of fault condition less than normal condition.

• Journal of the Korean Institute of Telematics and Electronics A
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• v.30A no.1
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• pp.64-72
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• 1993

We propose "algorithm MA" which can detect PSF that is the functional fault in RAM. This algorithm based on the restricted PSF(or neighborhood PSF) and can detect not only conventional stuck-at and transition faults but also SNPSF, PNPSF and partially ANPSF. The time complexity of "algorithm MA" has 1536xP(P=no. of partition). We propose total BIST(built-in self test) scheme which implement this algorithm in memory chip.ithm in memory chip.

• Proceedings of the Korean Institute of Intelligent Systems Conference
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• 2006.11a
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• pp.163-166
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• 2006

유도전동기는 산업시스템에 있어서 필수적인 요소이기 때문에 유지 관리, 모니터링시스템, 고장 진단 등의 다양한 분야에서 많은 연구가 행해지고 있다. 유도전동기의 운전 중 하나의 고장이 발생한 경우 이것은 전동기의 다른 부분에 영향을 미치거나 또 다른 고장을 유발시키는 원인이 된다. 따라서 개별적인 고장뿐만 아니라 결합된 형태의 고장을 검출하고 진단하는 것은 유용한 방법이다. 본 논문에서는 전압불평형 고장과 회전자바 고장이 발생한 경우, 그리고 두 고장이 동시에 복합적으로 발생한 경우를 모델링하고 이에 대해 고장 진단을 하였다. 제안된 고장 검출 및 진단 알고리즘은 농형운도전동기의 고정자 전류를 이용하였으며 매트랩 시뮬링크를 사용하여 시뮬레이션 하였다.

• Journal of the Institute of Electronics Engineers of Korea SD
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• v.38 no.2
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• pp.59-59
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• 2001

조합회로에 대한 ATPG 알고리듬이 효율적으로 100%의 고장 검출율을 달성할 수 있게 되어 감에 따라서 고장 검출율을 그대로 유지한 상태에서 테스트 패턴을 줄이는 압축 기법의 중요성이 점차로 부각되고 있다. 본 논문에서 제시하는 알고리듬은 고장들간의 독립과 양립 관계에 기초해서, 압축된 테스트 패턴을 위해서는 양립할 수 있는 고장 집합의 크기를 크게 해야 하므로, 고장-패턴 쌍과 고장들간의 독립과 양립 관계를 이용해서 고장-패턴 쌍의 트리 구조를 생성하였다. 이 고장-패턴 트리를 바탕으로 해서 효율적으로 압축된 테스트 패턴을 생성할 수 있었고, ISCAS 85와 ISCAS 89 측정 기준 회로에 대한 결과로 제시된 알고리듬의 우수성을 검증하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.11
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• pp.999-1005
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• 2007

In case of an abnormal condition of control surface, the real-time estimation of aerodynamic derivatives are required for the reconfigurable control system to be flight for missions or return to the head office. The goal of this paper is to represent a technique of fault detection to the control surface as a base research to the fault tolerant control system for safety improvement of UAV. The real-time system identification for the fault detection to the control surface was applied with the recursive Fourier Transform and verified through the HILS and flight test. The failures of the control surface are detected by comparing the control derivatives in fault condition with the normal condition. As a result from the flight test, we have confirmed that the control derivatives of fault condition less than about 50% in the normal condition.

• Journal of the Korean Institute of Intelligent Systems
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• v.17 no.6
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• pp.760-765
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• 2007

The sensor network system which has limited resources is deployed in a wide area and plays an important role of gethering information and monitoring. Generally, fault of sensor nodes which was caused by limited resources and poor environment happens. Futhermore, this fault poses many problems related with required quality of whole network. In this paper, new fault detection algorithm which utilizes both consensus algorithm and localized faulty sensor detection scheme is proposed. To verify the feasibility of the proposed scheme, some simulation and experiment are carried out.

• Journal of the Institute of Electronics Engineers of Korea SD
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• v.37 no.11
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• pp.105-114
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• 2000

Delay testing is essential for assurance of digital circuits as the speed and the density of the circuits improve greatly. However, delay faults in sequential circuits cannot be detected easily due to the existence of state registers. To overcome this difficulty a new test method and algorithm are devised which can be used for both stuck-at testing and delay testing. To apply the new test method, a new scan flip-flop is implemented. Experimental results on ISCAS 89 benchmark circuits show that the number of testable paths can be increased drastically over conventional scan techniques.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.6 no.6
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• pp.873-878
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• 2002

Stator current spectrum by the fast Fourier transform (FFT) of current signals has been widely used for fault detection in induction motors. In this paper, we propose efficient rotor fault detection of Induction motors using stator current spectrum monitoring. The proposed method utilizes the mean absolute difference (MAD) between a Predetermined reference vector and a feature vector extracted from the stator current spectrum. Our proposed approach requires a smaller amount of computations when compared to fault detection algorithms based on neural networks, since it uses simple MAD criterion to detect rotor faults related broken rotor bars. Experimental results show that our proposed method can successively detect the rotor fault of the induction motor.