• Journal of IKEEE
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• v.23 no.1
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• pp.266-272
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• 2019

Multicopters have become more popular since they are advantageous in their ability to take off and land vertically. In order to guarantee the normal operations of such multicopters, the problem of fault detection and isolation is very important. In this paper, a new method for detecting and isolating an actuator fault of a hexacopter is proposed based on the analytical approach. The residual is newly defined using the angular velocities of actuators estimated by the mathematical model and an actuator fault is detected comparing the residuals to a threshold. And a fault is isolated combining a dynamic model and generated residuals when a fault is detected. The proposed method is a simple, but effective technique because it is based on mathematical model. The results of the computer simulation are also given to demonstrate the validity of the proposed algorithm in case of a single failure.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.3
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• pp.57-64
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• 2005

In two-degree of freedom(TDOF) inertial sensors, two axes are mechanically correlated with each other. Fault source of one axis sensor may affect the other axis sensor, and therefore multiple fault detection and isolation(FDI) technique is required. Conventional FDI techniques using hardware redundancy need four TDOF inertial sensors for FDI. In this study, three TDOF inertial sensor redudancy case is considered, where conventional FDI technique can detect the fault, but cannot isolate the fault sensor. Hybrid FDI technique is proposed to solve this problem. Hybrid FDI technique utilizes the analytic redundancy by utilizing the unscented kalman filter as well as hardware redundancy for FDI. To verify the effectiveness of the proposed FDI technique, numerical simulations are performed using six degree of freedom nonlinear aircrft dynamics.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.11
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• pp.943-951
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• 2015

Inertial sensors are important components of navigation system whose performance and reliability can be improved by specific sensor arrangement configuration. For the reliability of the system, Fault Detection and Isolation (FDI) is conducted by comparing each signal of arranged sensors and many arrangement configuration were suggested to optimize FDI performance of the system. In this paper, multiple conic configuration is suggested with optimal navigation condition and its FDI performance is analyzed by established Figure Of Merit (FOM) under the condition for navigation optimality. From FOM comparison, the multiple conic configuration is superior to former one in point of FDI.

• 전기의세계
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• v.40 no.3
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• pp.57-61
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• 1991

계통에 대한 정보, 즉 구간의 부하 상태, 차단기 및 스위치들의 현 개폐상태, 그리고 고장 검출기 동작상태 등은 통신망을 통하여 중앙 제어소로 전송되어지며 계통운용의 책임을 지고 있는 오퍼레이터(operator)는 이들 정보를 근거로 하여 계통의 현 상황을 파악하여 적절한 조치를 취하게 된다. 좀 더 자세히 말하면, 먼저 고장이 발생하지 않은 평상시(normal state)에는 계통의 부하 상태를 감시하여 운전손실 및 전압강하를 최소화 하는 계통으로의 변경을 원격조정 스위치 조작을 통하여 쉽고도 신속하게 실행시킴으로써 보다 효율적이고 경제적인 계통운전을 이룩할 수 있게 될 것이다. 또한 선로에 고장이 발생했을 경우, 변전소 차단기가 트립되기 전의 고장전류를 경험하게 되는 위치에 있는 스위치의 고장 검출요소(FD)가 동작하게 되며, 이러한 고장 검출기 동작상태, 스위치들의 현 개폐 상태 및 차단기의 트립 정보등은 중앙 제어소로 전송되어지며 오퍼레이터는 이들 정보로부터 고장구간을 판별하여 원격 조정 스위칭을 통하여 고장구간을 신속히 분리시키고, 정전구역에 대하여 운전 제약 조건을 위반하지 않는 복구계획을 수립하여 실행함으로써 보다 빠른 고장 위치 판단과 사고복구를 실현할 수 있으며 수용가의 공급 지장 시간을 최대한도로 줄여 배전 계통의 공급신뢰도를 높일 수 있다. 고장 발생시 이와 같은 일련의 과정은 크게 고장 구간 판별(Fault Location Identification) 및 정전 복구(Service Restoration)로 나눌 수 있으며 각각에 대하여 다음에 기술한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.12
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• pp.1225-1231
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• 2009

One reaction wheel cluster of satellite usually has four reaction wheels. Each wheel is not arranged parallel to the attitude axis of satellite. Therefore, if one reaction wheel is broken, it is very hard to isolate the fault except using the sensors of wheel itself. In this paper, the isolator of satellite reaction wheel cluster is designed. Using a dual filter, FDP(Fault Detection Parameter) is made to detect fault, and using a multi-hypothesis extended Kalman filter, fault isolation of wheel cluster is done. We verify the improvement of isolation performance of wheel cluster by simulation with 4-reaction wheel cluster.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.12
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• pp.1040-1047
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• 2012

This paper presents a fault diagnosis algorithm of control surfaces of small fixed-wing aircraft to reduce maintenance cost or to improve repair efficiency by estimation of fault occurrence or part replacement periods. The proposed fault diagnosis algorithm consists of ANPSD (Averaged Normalized Power Spectral Density), PCA (Principle Component Analysis), and GC (Geometric Classifier). ANPSD is used for frequency-domain vibration testing. PCA has advantage to extract compressed information from ANPSD. GC has good properties to minimize errors of the fault detection and isolation. The algorithm was verified by the accelerometer measurements of the scaled normal and faulty ailerons and the test results show that the algorithm is suitable for the detection and isolation of the control surface faults. This paper also proposes solutions for some kind of implementation problems.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.150-156
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• 2007

In this paper, we focus on the fault detection and isolation(FDI) method for inertial navigation system with three two-degree of freedom dynamically tuned gyros(DTG) on orthogonal sensor configuration. we propose the FDI method which can detect the fault of each DTGs rather than the fault of each sensing axis. The proposed FDI method is separated into two FDI modules according to the fault magnitude in order to improve the reliability of fault detection information. For large fault detection, only instantaneous DTG measurement is used to detect a fault DTG within a short time. For small fault detection, the integrated value of DTG measurements are used to detect a fault DTG. It takes a more time to detect a fault but it serves more reliable fault detection information. Using the proposed FDI method with consideration of DTG fault characteristic, we could find out a fault DTG successfully.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.9
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• pp.72-79
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• 2004

A method for thruster fault diagnosis for launch vehicle upper stage was developed. In order to protect the launch vehicle against the occurrence of faults, it is necessary to detect and identify the fault, as well as to reconfigure the controller of the vehicle. Considering the upper stage launch vehicle using reaction control system, an analytical method was adopted in order to detect the fault occurred in thruster. The fault detection scheme can be applied to the system regardless of the form of thruster fault occurred - leakage or lock-out. Results from processor-in-the-loop simulation are provided to demonstrate the validity of this fault detection and isolation scheme for the upper stage launch vehicle.

• Journal of the Korea Institute of Military Science and Technology
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• v.7 no.3 s.18
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• pp.140-148
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• 2004

Fault detection and isolation(FDI) and reconfigurable flight control system provide better survivability even though actuator faults occur. In this study, a new fault detection and isolation algorithm is proposed using fuzzy logic. When the FDI system detects the actuator fault, the fuzzy logic investigates the state variables to find which actuator has fault. Proposed fuzzy detection algorithm detect not only a single fault but also multiple faults. After detecting the fault, the reconfigurable flight control system begins operating for compensating the effects of the fault. A numerical simulation using six degree-of-freedom nonlinear aircraft model is performed to verity the performance of the proposed fault detection and isolation scheme.

• Proceedings of the Korea Contents Association Conference
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• 2016.05a
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• pp.425-426
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• 2016

ICT(Information and Communications Technologies)의 빠른 발전으로 직류 전원의 직접 사용이 증가하고 있다. 그러나 대용량 가변가능 직류 전원 장치가 보편화되지 않았으며 현재 ICT 기기들은 내부 또는 외부에 직류 전원 정류 장치를 내장하고 있다. 앞으로 더욱더 많은 기기들이 교류 전원이 아닌 직류 전원을 사용하게 되므로 가변이 가능한 대용량의 직류 전원 장치가 필요하게 될 것이다. 그러나 가변 가능한 구조의 전원장치는 다수의 전원 장치를 병렬로 연결하여야 하므로 고장에 대한 검출 및 분리가 필요하게 된다. 이러한 고장 검출을 위하여 확장 패리티 공간 기법을 적용하였다.