• 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.

• 제어로봇시스템학회:학술대회논문집
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• 2000.10a
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• pp.130-130
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• 2000

This paper presents a robust fault diagnosis and fault tolerant control lot the actuator and sensor faults in the closed-loop systems affected by unknown inputs or disturbances. The fault diagnostic scheme is based on the residual set generation by using robust Parity space approach. Residual set is evaluated through the threshold test and then fault is isolated according to the decision logic table. Once the fault diagnosis module indicates which actuator or sensor is faulty, the fault magnitude is estimated by using the disturbance-decoupled optimal state estimation and a new additive control law is added to the nominal one to override the fault effect on the system. Simulation results show that the method has definite fault diagnosis and fault tolerant control ability against actuator and sensor faults.

• ICROS
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• v.6 no.4
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• pp.38-48
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• 2000

Abstract :본 논문에서는 관리제어시스템의 동적특성을 허용언어(admissible language) 범위 이내에서 최적화시키는 최적 관리제어기법들을 소개한다. 본 논문에서 주로 다루고자 하는 최적 관리제어기법은 Kumar와 Garg에 의해 제안된 기법과 Cho와 Lim에 의해 제안된 계층적 최적 관리제어기법, 그리고, Sengupta와 Lafortune이 제안한 최적 관리제어기법 등이다. 첫 번째 기법에서는 우선 시스템의 최적화를 위해 고려되고 있는 비용함수(cost function)를 소개한 후, 최대흐름 최소분할생성 정리(max-flow min-cut theorem)를 이용한 최적 관리제어기 설계기법을 제시하고, 이를 부분관측 하에서도 최적 관리제어기를 설계할 수 있도록 확장한다. 그런 후 제시된 설계기법에 의해 설계된 관리제어시스템에서 발생 할 수 있는 문제점들을 지적하고, Cho와 Lim에 의해 제안된 완전 최소분할생성(complete min-cut)이라는 개념을 도입하여 지적된 문제점들을 해결할 수 있는 방법을 제시한다. 또한 시스템의 고장을 고려한 계층적 최적 관리 제어(layered optimal supervisory control)기 법을 소개한다 그리 고 마지막으로 Sengupta와 Lafortune이 제안한 최적 관리제어기법에 대해서 살펴본다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.9
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• pp.627-638
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• 2022

This paper discusses the utilization of fault-tolerant technology in the industry by analyzing the status of drone failures in the unmanned vehicle industry survey conducted in 2020. Based on the survey results of the domestic unmanned vehicle industry, we identify subsystems with high fault rates and high severity when faults occur. In addition, fault simulations of the identified subsystems are conducted to analyze the effect of the fault on the vehicles. After that, the fault diagnosis and fault compensation methods studied so far are reviewed, and research cases of the methods are examined. Moreover, the ways to apply it to actual fault cases in the unmanned vehicle industry are debated. Furthermore, based on the previous discussion, the fault-tolerant system is presented, and the consideration when designing the fault-tolerant system in the industry are studied.

• Journal of Applied Reliability
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• v.12 no.3
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• pp.215-224
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• 2012

This paper deals with a design of fault tolerant state feedback controllers for continuous time nonlinear time delay systems with actuator failures. The goal is to find an asymptotically stabilizing controller such that the closed loop system achieves the prescribed $H_{\infty}$ performance objective in the actuator fault cases. Based on a sum of squares (SOS) approach, a design method for $H_{\infty}$ fault tolerant controller is presented. In order to demonstrate our design method, a numerical example is provided.

• Journal of Aerospace System Engineering
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• v.11 no.5
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• pp.28-35
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• 2017

Magnetic Suspension and Balance System (MSBS) demonstrates the capacity to levitate an experimental model absent any mechanical contact using magnetic forces and moments. It allows precise control of position and attitude of the model, and measures external forces and moments acting on the model. For the purpose of acquisition of reliable experimental results under stable and safe conditions, the performance and robustness of the position and attitude control system of MSBS needs to be improved. To this end, Iterative Feedback Tuning (IFT) and L1 adaptive output feedback algorithm were employed to automatically increase command following performance and to ensure robust operation of MSBS with failure of electric power supply. The applicability was validated using computational simulation.

• Journal of Aerospace System Engineering
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• v.13 no.4
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• pp.50-59
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• 2019

The design of the main control valve, which is the main component of the flap control system, was based on actual manufacturing experience on the basis of trial and error method. In this paper, a model-based part design method is proosed. The flap control system consists of a main control valve, fail-safe valve, solenoid valve, LVDT and force motor. The main control valve consists mainly of a spool and slot. The important design parameters of the main control valve are the slot width, overlap and clearance. AMESim is linked to the model and it analyzes the flow path of the main control valve. Applying the proposed design procedure, it was confirmed that the required performance was satisfied within the allowable machining error range.

• Journal of Institute of Control, Robotics and Systems
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• v.9 no.2
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• pp.107-116
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• 2003

This paper presents a systematic design methodology for fault tolerant controller against a fault in actuators and sensors of linear stochastic systems with uncertainties. The scheme is based on fault detection and diagnosis(isolation and estimation) using a bank of robust two-stage Kalman filters, and accommodation of the actuator fault by eigenstructure assignment and immediate compensation of the sensor's faulty measurement. In order to clarify the fault feature in test statistics of residual, noise reduction method is given by multi-scale discrete wavelet transform. The effectiveness of our approach Is shown via simulations for a VTOL(vertical take-off and landing) aircraft subjected to parameter variations, external disturbances, process and sensor noises.

• The Transactions of the Korean Institute of Electrical Engineers A
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• v.48 no.10
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• pp.1259-1263
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• 1999

In this paper, a method to guarantee system continuity is developed, which can be applied to discontinuity problem in the time domain of restructurable control system. This method can be summarized as input alternation using weight change considering convergence speed of system mode. Input is changed from 'system continuity guarantee input,' which is defined as a input that minimizes the change of state variables, to 'alternative controller input,' which is selected by Neil's PI/EAM[3]. AIDC aircraft model is used for simulation. By showing the waveform of system input and state variable, we can sure that this method is effective for depression of system shock like jerk.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.21 no.7
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• pp.1765-1776
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• 1996

클라이언트=서버 DBMS구조는 많은 사람들에 의해서 연구되고 있으나 고장회복과 동시성 제어에 관한 연구는 아직까지 미흡한 상태다. 기존의 회복 기법은 클라이언트에서 생성된 로그 레코드들과 해당 데이터 페이지들을 서버에 전송 함으로써 발뱅하는 문제점들에 대한 해결점이 필요하였다. 본 논문에서는 클라이언트가 서버에 수행 완료된 로그 레코드들만을 전송하여 기존의 회복 기법에서 발생하였던 문제점을 제거한다. 또한 서버는 수행 완료된 로그 레코드들만을 관리하여 서버 파손 발생시 분석, 재수행 동작만을 수행하는 간단한 회복 알고리즘을 제안한다. 클라이언트에서 철회 동작을 함으로써 시스템의 병렬성을 높이고 서버 파손시 전체 데이터베이스 회복에 소요되는 시간을 줄이기 위해서 페이지 단위의 회복 기법도 제안한다. 또한 기존의 동시성 제어기법은 같은 페이지를 동시 사용하지 못함으로써 불필오한 대기시간(waiting time)이 증가된다. 본 논뭉에서는, 기존의 기법과 달리, 같은 페이지 내에 다른 데이터를 접근하는 트랜잭션에게 페이지를 허용함으로써 불필요한 대기시간을 최소화 할 수 있도록 하여 시스템의 병렬성을 향상시켰다.