scholarly journals Model Based Fuzzy Logic Sensor Fault Accommodation

1997 ◽  
Author(s):  
Timothy A. Healy ◽  
Laura J. Kerr ◽  
Louis J. Larkin
Keyword(s):  
Fuzzy Logic ◽  
Fault Isolation ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Sensor Faults ◽  
Fault Accommodation ◽  
Engine Model ◽  
Dual Channel ◽  
Sensor Channel ◽  
Channel Control

Sensor in-range fault accommodation is a fundamental challenge of dual channel control systems in modem aircraft gas turbine engines. An on-board real-time engine model can be used to provide an analytical third sensor channel which may be used to detect and isolate sensor faults. A fuzzy logic based accommodation approach is proposed which enhances the effectiveness of the analytical third channel in the control system’s fault isolation and accommodation scheme. Simulation studies show the fuzzy accommodation scheme to be superior to current accommodation techniques.

Model Based Fuzzy Logic Sensor Fault Accommodation

1998 ◽  
Vol 120 (3) ◽  
pp. 533-536 ◽  
Author(s):  
T. A. Healy ◽  
L. J. Kerr ◽  
L. J. Larkin
Keyword(s):  
Fuzzy Logic ◽  
Fault Isolation ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Sensor Faults ◽  
Fault Accommodation ◽  
Engine Model ◽  
Dual Channel ◽  
Sensor Channel ◽  
Channel Control

Sensor in-range fault accommodation is a fundamental challenge of dual channel control systems in modern aircraft gas turbine engines. An on-board, real-time engine model can be used to provide an analytical third sensor channel that may be used to detect and isolate sensor faults. A fuzzy-logic-based accommodation approach is proposed that enhances the effectiveness of the analytical third channel in the control system’s fault isolation and accommodation scheme. Simulation studies show the fuzzy accommodation scheme to be superior to current accommodation techniques.

A Unified Nonlinear Approach to Fault Diagnosis of Aircraft Engines

2013 ◽  
Author(s):  
Xiaodong Zhang ◽  
Remus C. Avram ◽  
Liang Tang ◽  
Michael J. Roemer
Keyword(s):  
Fault Detection ◽  
Adaptive Estimation ◽  
Fault Isolation ◽  
Nonlinear Observer ◽  
Aircraft Engines ◽  
Sensor Faults ◽  
Actuator Faults ◽  
Engine Model ◽  
Fault Type ◽  
Component Faults

Many existing aircraft engine diagnostic methods are based on linearized engine models. However, the dynamics of aircraft engines are highly nonlinear and rapidly changing. Future engine health management designs will benefit from new methods that are directly based on intrinsic nonlinearities of the engine dynamics. In this paper, a fault detection and isolation (FDI) method is developed for aircraft engines by utilizing nonlinear adaptive estimation and nonlinear observer techniques. Engine sensor faults, actuator faults and component faults are considered under one unified nonlinear framework. The fault diagnosis architecture consists of a fault detection estimator and a bank of nonlinear fault isolation estimators. The fault detection estimator is used for detecting the occurrence of a fault, while the bank of fault isolation estimators is employed to determine the particular fault type or location after fault detection. Each isolation estimator is designed based on the functional structure of a particular fault type under consideration. Specifically, adaptive estimation techniques are used for designing the isolation estimators for engine component faults and actuator faults, while nonlinear observer techniques are used for designing the isolation estimators for sensor faults. The FDI architecture has been integrated with the Commercial Modular Aero-Propulsion System Simulation (C-MAPSS) engine model developed by NASA researchers in recent years. The engine model is a realistic representation of the nonlinear aero thermal dynamics of a 90,000-pound thrust class turbofan engine with high-bypass ratio and a two-spool configuration. Representative simulation results and comparative studies are shown to verify the effectiveness of the nonlinear FDI method.

scholarly journals РЫНОК И ПЕРСПЕКТИВЫ ЛЕГКИХ ВЕРТОЛЕТОВ С ГАЗОТУРБИННЫМИ ДВИГАТЕЛЯМИ

2020 ◽  
pp. 5-12
Author(s):  
Вадим Владимирович Нерубасский
Keyword(s):  
Gas Turbine ◽  
World Market ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
New Developments ◽  
Dual Channel ◽  
Engine Industry ◽  
Main Activity ◽  
Rotary Wing

In the introductory part of the article, it is provided brief information about the main activity of JSC “Element”- developer and manufacturer of electronic control systems for aircraft engines, in particular unit RDTs-450M for AI-450M helicopter turboshaft gas turbine engines, created by SE “Ivchenko-Progress”. JSC ”Element”, together with its partners - SE “Ivchenko-Progress” and  JSC “Motor-Sich” – for more than 10 years involved in the modernization of Mi-2 light helicopter.In the next section is gave the classification of helicopters, as well as a segment of light helicopters with turbine engines. It is outlined the scope of light helicopters. It is noted that the segment of light helicopters with turbine engines – the most popular in the world market of civil helicopters and provides a forecast of the supply of these helicopters for the next 10 years.Lists the world's major developers and manufacturers of light helicopters, and the technical characteristics of 12 models of light helicopters with turbine engines are depicted. It is noted that most helicopter models are not entirely new developments and have been modernized over many years. The characteristic design features of light helicopters with turbine engines, especially the layout of plant and equipment are depicted. There is a trend of using one model of helicopter multiple engine types.Lists the world's major developers and manufacturers of engines for light helicopters, as well as the technical characteristics of the six models of gas turbine engines are depicted. The main structural and compositional features of gas-turbine engines of different manufacturers and types of a helicopter on which they installed are described. Separately, brief information about the Ukrainian gas-turbine engines: AI-450M and MS-500V. It is noted that all, without exception, mentioned in the article, engines are equipped with a digital single or dual-channel FADEC type control system with hydro-mechanical redundancy.Brief information about individual conceptual samples of rotary-wing technology introduced in recent years is given. The main directions of work in the field of helicopter engines are described.In conclusion, the Ukrainian helicopter and Aero-engine industry are in a difficult economic situation, but remain competitive and require assistance and the expansion of the market.

scholarly journals Інтелектуальний регулятор запасу газодинамічної стійкості компресора авіаційного ГТД

2021 ◽  
pp. 48-52
Author(s):  
Сергій Васильович Єнчев ◽  
Сергій Олегович Таку
Keyword(s):  
Fuzzy Logic ◽  
Nonlinear Systems ◽  
Fuzzy Control ◽  
Control Systems ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Harmonic Linearization ◽  
Gas Dynamic

The gas-dynamic stability of compressors of aircraft gas turbine engines is one of the most important conditions that determine their reliability and level of flight safety. Unstable operation of the compressor in the engine system (surge) leads to loss of thrust accompanied by an increase in gas temperature in front of the turbine and increased vibration because of large amplitudes of pressure pulsations and mass flow through the engine path. To improve the parameters of ACS aviation gas turbine engines are increasingly using regulators built using fuzzy logic algorithms. The implementation of fuzzy control algorithms differs from classical algorithms, which are based on the concept of feedback and reproduce a given functional dependence or differential equation. These functions are related to the qualitative assessment of system behavior, analysis of the current changing situation, and the selection of the most appropriate for the situation supervision of the gas turbine engine. This concept is called advanced management. ACS gas turbine engines with fuzzy regulators are nonlinear systems in which stable self-oscillations are possible. Approximate methods are used to solve the problems of analysis of periodic oscillations in nonlinear systems. Among them, the most developed in theoretical and methodological aspects is the method of harmonic linearization. The scientific problem is solved in the work – methods of synthesis of intelligent control system with the fuzzy regulator as a separate subsystem based on the method of harmonic linearization and design on its basis of fuzzy ACS reserve of gas-dynamic stability of aviation gas turbine engine. Based on the analysis of the principles of construction of fuzzy control systems, it is shown that the use of fuzzy logic provides a new approach to the design of control systems for aviation gas turbine engines in contrast to traditional control methods. It is shown that the fuzzy controller, as the only essentially nonlinear element when using numerical integration methods, can be harmonically linearized. Harmonic linearization allows using the oscillation index to assess the quality in the separate channels of fuzzy ACS aviation gas turbine engines. A fuzzy expert system has been developed for optimal adjustment of the functions of belonging of typical fuzzy regulators according to quality criteria to transients.

scholarly journals An Adaptive Model-Based Framework for Prognostics of Gas Path Faults in Aircraft Gas Turbine Engines

2019 ◽  
Vol 10 (2) ◽  
Author(s):  
Ogechukwu Alozie ◽  
Yi-Guang Li ◽  
Xin Wu ◽  
Xingchao Shong ◽  
Wencheng Ren
Keyword(s):  
Gas Turbine ◽  
Fault Isolation ◽  
Performance Model ◽  
Remaining Useful Life ◽  
Operating Conditions ◽  
Sensor Data ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Degradation Models ◽  
Useful Life

This paper presents an adaptive framework for prognostics in civil aero gas turbine engines, which incorporates both performance and degradation models, to predict the remaining useful life of the engine components that fail predominantly by gradual deterioration over time. Sparse information about the engine configuration is used to adapt a performance model, which serves as a baseline for implementing optimum sensor selection, operating data correction, fault isolation, noise reduction and component health diagnostics using nonlinear Gas Path Analysis (GPA). Degradation models, which describe the progression of faults until failure, are then applied to the diagnosed component health indices from previous run-to-failure cases. These models constitute a training library from which fitness evaluation to the current test case is done. The final remaining useful life (RUL) prediction is obtained as a weighted sum of individually evaluated RULs for each training case. This approach is validated using dataset generated by the Commercial Modular Aero-Propulsion System Simulation (CMAPSS) software, which comprises both training and testing instances of run-to-failure sensor data for a turbofan engine, some of which are obtained at different operating conditions and for multiple fault modes. The results demonstrate the capability of improved prognostics of faults in aircraft engine turbomachinery using models of system behavior, with continuous health monitoring data.

scholarly journals Integration of On-Line and Off-Line Diagnostic Algorithms for Aircraft Engine Health Management

2007 ◽  
Author(s):  
Takahisa Kobayashi ◽  
Donald L. Simon
Keyword(s):  
Gas Turbine ◽  
Health Management ◽  
Diagnostic Algorithm ◽  
Aircraft Engine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Simulation Environment ◽  
Diagnostic Algorithms ◽  
Engine Model ◽  
On Line

This paper investigates the integration of on-line and off-line diagnostic algorithms for aircraft gas turbine engines. The on-line diagnostic algorithm is designed for in-flight fault detection. It continuously monitors engine outputs for anomalous signatures induced by faults. The off-line diagnostic algorithm is designed to track engine health degradation over the lifetime of an engine. It estimates engine health degradation periodically over the course of the engine’s life. The estimate generated by the off-line algorithm is used to “update” the on-line algorithm. Through this integration, the on-line algorithm becomes aware of engine health degradation, and its effectiveness to detect faults can be maintained while the engine continues to degrade. The benefit of this integration is investigated in a simulation environment using a nonlinear engine model.

Fuzzy robust fault estimation scheme for fault tolerant flight control systems based on unknown input observer

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Gulay Unal
Keyword(s):  
Fuzzy Logic ◽  
Control System ◽  
Fault Detection ◽  
Flight Control ◽  
Fault Tolerant ◽  
Fault Isolation ◽  
Fault Detection And Isolation ◽  
Sensor Faults ◽  
Flight Control System ◽  
Content Type

Purpose The purpose of this study is to present a new integrated structure for a fault tolerant aircraft control system because fault diagnosis of flight control systems is extremely important in obtaining healthy flight. An approach to detect and isolate aircraft sensor faults is proposed, and a new integrated structure for a fault tolerant aircraft control system is presented. Design/methodology/approach As disturbance and sensor faults are mixed together in a flight control system, it is difficult to isolate any fault from the disturbance. This paper proposes a robust unknown input observer for state estimation and fault detection as well as isolation using fuzzy logic. Findings The dedicated observer scheme (DOS) and generalized observer scheme (GOS) are used for fault detection and isolation in an observer-based approach. Using the DOS, it has been shown through simulation that sensor fault detection and isolation can be made, but here the threshold value must be well chosen; if not, the faulty sensor cannot be correctly isolated. On the other hand, the GOS is more usable and flexible than the DOS and allows isolation of faults more correctly and for a fuzzy logic-based controller to be used to realize fault isolation completely. Originality/value The fuzzy logic approach applied to the flight control system adds an important key for sensor fault isolation because it reduces the effect of false alarms and allows the identification of different kinds of sensor faults. The proposed approach can be used for similar systems.

Selection of Outputs for Gas-Turbine Engines by Parameter Signatures

2010 ◽  
Author(s):  
James R. McCusker ◽  
Kourosh Danai
Keyword(s):  
Nonlinear Least Squares ◽  
Turbine Engines ◽  
Model Parameters ◽  
Gas Turbine Engines ◽  
Jet Engines ◽  
Estimation Of Parameters ◽  
Output Measurement ◽  
Engine Model ◽  
Measurement Selection ◽  
Selection Of

A method of measurement selection is introduced that relies on parameter signatures to assess the identifiability of dynamic model parameters by different outputs. A parameter signature is a region in the time-scale plane wherein the sensitivity of the output with respect to one model parameter is much larger than the rest of output sensitivities. Since the existence of a parameter signature is synonymous with the uniqueness of the corresponding output sensitivity, parameter signatures are directly linked to parameter identifiability by outputs and, hence, can be used for output/measurement selection. The purpose of this paper is to introduce a strategy for measurement selection by parameter signatures and to demonstrate its applicability to the transient decks of turbo-jet engines. The validity of the selected outputs in providing observability to the engine model parameters is independently verified by successful estimation of parameters by nonlinear least-squares.

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