• Journal of IKEEE
• /
• v.25 no.2
• /
• pp.330-336
• /
• 2021

A typical way to reduce the number of hardware redundancy configurations is to implement them as analytical techniques for detecting, identifying and accepting failures with micro-controller. In this paper, one of the analytical techniques, the fault detection filter, is applied to aircraft turbofan engine system. The fault detection filter is a special type of observer that has the advantage of being able to determine the location of failures by maintaining a constant direction in the output space in the event of a particular failure. We present a single input/output dynamic system modeling of air turbine system in turbofan engine, a fault detection filter design, and simulation results applying it. Simulation results show that fault detection can be effectively applied as a sensitivity effect to the directionality of the detection filter.

• ICROS
• /
• v.16 no.2
• /
• pp.33-36
• /
• 2010

최근 다양하고 복잡한 산업 구조로 인하여 인적 물적 피해가 큰 대형 사고가 자주 발생하고 있으며 산업 전반에 신뢰성과 안전성 확보가 중요한 문제로 부각되고 있다. 산업이 전반적으로 복잡해 지고 그 시스템의 규모가 대규모로 진행됨에 따라 자동화된 장비의 사용이 빈번해 졌으며, 시스템의 고장을 유발하는 요인이 다양해 지고 고장의 발생 빈도 역시 증가하였다. 고장은 시스템의 정상운영을 저해하기도 하며, 사회적으로 큰 경제적인 손실을 가져다 주기도 한다. 고장의 영향을 최소화하기 위하여 고장검출 및 대응 기술이 필요하며, 고장검출과 관련된 이론의 고찰은 매우 중요하다. 고장검출 관련 이론은 다양한 분야에서 활용도고 있으나, 처음으로 접하는 단계에서는 그 이해에 어려움을 느낄 수 있다. 본 자료는 고장검출 관련 이론을 처음 접하는 독자에게 이를 쉽게 설명하는데 그 목적이 있으며, 고장검출 관련 기본이론과 고장검출에 많이 쓰이고 있는 고장검출 필터의 개념을 비교적 간결하게 설명하고 있다.

• ICROS
• /
• v.17 no.4
• /
• pp.42-45
• /
• 2011

위성 구동기 고장을 검출하는 문제를 살펴보기 위하여, 최근에 발표된 논문을 분석하였다. 구동기에 발생하는 고장은 그 영향이, 위성의 동역학을 거쳐서 센서의 출력으로 나타나기 때문에, 고장 검출은 기본적으로 상태추정이 수반되어야 한다. 다양한 상태추정기법이 적용될 수 있는데, 가장 많이 사용되는 기법은 Kalman 필터 및 유사 필터들이다. 위성의 고장에 적시에 대응한다면 피해를 최소화할 수 있기 때문에, 자율성 높은 탑재형(on-board)의 고장 진단 및 대응 시스템이 주요 연구목표가 된다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.37 no.12
• /
• pp.1225-1231
• /
• 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 Institute of Intelligent Systems
• /
• v.25 no.6
• /
• pp.615-620
• /
• 2015

This paper deals with a fault detection system design for a boiler-turbine control system of thermal power plant. We described the nonlinear properties of the boiler-turbine dynamics as a T-S fuzzy system with time varying measurable parameters. We design a residual generator using an observer based fault detection filter. In order to identify the faulted output sensor, an approximate inverse system is connected to the outport of the fault detection filter. We demonstrate the efficiency of the suggested design method via computer simulations.

• Proceedings of the IEEK Conference
• /
• 2001.06e
• /
• pp.55-58
• /
• 2001

본 논문에서는 해석적인 모델에 기초한 고장 검출 기법의 하나인 fault detection filter를 적용한 고장 검출 알고리듬을 개발하고 이를 적용하여 고장검출 필터의 유효성을 보이고자 한다. Fault detection filter는 특수한 형태의 observer로써 특정한 고장의 발생시 잔차가 출력 공간에서 일정한 방향을 유지함으로써 고장 개소의 판별이 가능하다. 이에 본 논문에서는 fault detection filter에 기초한 고장 감지 시스템을 적용하기 위한 다이나믹 시스템 모델링과 고장감지 시스템의 설계과정 및 이를 적용 모의시험 결과를 수록하였다. 결과를 통하여 fault detection filter가 갖는 방향성에 대한 sensitivity 효과를 고장 감지 목적에 유효하게 적용할 수 있음을 보였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2008.11a
• /
• pp.192-195
• /
• 2008

A sensor fault detection method for small turbo shaft engine considering multiple trim conditions is proposed. This engine is used in a helicopter. Firstly, under multiple trim conditions, we derive the linearized models from a nonlinear model which includes engine, rotor and feedback control loop. As a fault detection method, we adopt the Kalman filter based method. To keep continuity of estimates between the changes of trim conditions, we reconfigure the initial values of state variables at trim changes. We detect the faults with two steps that when the first filter does not alarm the faults for some sensors, the second filter is runned for other sensor. Via some simulations we show that the proposed method works well under multiple trim conditions.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.33 no.3
• /
• pp.57-64
• /
• 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
• /
• v.39 no.2
• /
• pp.144-152
• /
• 2011

This paper presents a new scheme for fault detection and isolation in the satellite system. The purpose of this paper is to develop a fault detection, isolation and diagnosis algorithm based on the bank of interacting multiple model (IMM) filter for both total and partial faults in a satellite attitude control system (ACS). In this paper, IMM are utilized for detection and diagnosis of anticipated actuator faults in a satellite ACS. Other fault detection, isolation (FDI) schemes using conventional IMM are compared with the proposed FDI scheme. The FDI procedure is developed in two stages. In the first stage, 11 EKFs actuator fault models are designed to detect wherever actuator faults occur. In the second stage of the FDI scheme, two filters are designed to identify the fault type which is either the total or partial fault. An important feature of the proposed FDI scheme can decrease fault isolation time and figure out not only fault detection and isolation but also fault type identification.

• Journal of the Korean Institute of Intelligent Systems
• /
• v.16 no.2
• /
• pp.191-197
• /
• 2006

This paper deals with a fault detection system design for nuclear steam generator water level control system. We expressed the nonlinear properties of the steam generator level system as a T-S fuzzy system with time varying uncertain parameters. We design a residual generator using a left coprime factorization of the T-S fuzzy model and a fault detection filter in order to improve the fault detection performance. We demonstrate the efficiency of the suggested design method via many computer simulations.