Robust fault detection of dynamic systems via genetic algorithms

1997 ◽  
Vol 211 (5) ◽  
pp. 357-364 ◽  
Author(s):  
R J Patton ◽  
J Chen ◽  
G P Liu
Keyword(s):  
Genetic Algorithm ◽  
Fault Detection ◽  
Flight Control ◽  
Optimal Solution ◽  
Inequality Constraints ◽  
Performance Indices ◽  
Frequency Distributions ◽  
Modelling Uncertainty ◽  
Detection Systems ◽  
Robust Fault Detection

This paper presents a new approach to the design of robust fault detection systems via a genetic algorithm. To achieve robustness, a number of performance indices are introduced, which are expressed in the frequency domain to account for the frequency distributions of incipient faults, noise and modelling uncertainty. All objectives are then reformulated into a set of inequality constraints on performance indices. A genetic algorithm is thus used to search an optimal solution to satisfy these inequality constraints. The approach developed is applied to a flight control system example and results show that incipient sensor faults can be detected reliably in the presence of modelling uncertainty.

Knowledge-Based Automatic Fault Detection in Flight Control System

2007 ◽  
Author(s):  
C. H. Lo ◽  
Eric H. K. Fung ◽  
Y. K. Wong
Keyword(s):  
Genetic Algorithm ◽  
Genetic Algorithms ◽  
Control System ◽  
Fault Detection ◽  
Flight Control ◽  
Detection System ◽  
Flight Control System ◽  
Actuator Failure ◽  
Fuzzy Genetic Algorithm ◽  
Fuzzy Genetic

There are various possible failures, like, actuator, sensor, or structural, which can occur on a sophisticated modern aircraft. In certain situations the need for an automatic fault detection system provides additional information about the status of the aircraft to assist pilots to compensate for failures. In this paper, we develop an intelligent technique based on fuzzy-genetic algorithm for automatically detecting failures in flight control system. The fuzzy-genetic algorithm is proposed to construct the automatic fault detection system for monitoring aircraft behaviors. Fuzzy system is employed to estimates the times and types of actuator failure. Genetic algorithms are used to generate an optimal fuzzy rule set based on the training data. The optimization capability of genetic algorithms provides and efficient and effective way to generate optimal fuzzy rules. Different types of actuator failure can be detected by the fuzzy-genetic algorithm based automatic fault detection system after tuning its rule table. Simulations with different actuator failures of the non-linear F-16 aircraft model are conducted to appraise the performance of the proposed automatic fault detection system.

Robust Fault Detection for Network-Based System with Time-Varying Bounded Delay

2012 ◽  
Vol 503-504 ◽  
pp. 1389-1392
Author(s):  
Li Min Chen
Keyword(s):  
Fault Detection ◽  
Flight Control ◽  
Upper Bound ◽  
Filter Design ◽  
Estimation Error ◽  
Linear Matrix ◽  
Fault Detection Filter ◽  
Detection Approach ◽  
Robust Fault Detection ◽  
Detection Filter

A robust fault detection approach for network-based system is discussed in this paper. The fault detection problem is converted into fault detection filter design. The network-induced delay is assumed to have both the upper bound and the lower bound, which is more general compared with only considering the upper bound. The Lyapunov-Krasovskii functional and the linear matrix inequality (LMI)-based procedure are adopted to design the filter. And the filter can guarantee that the estimation error satisfies the H∞ constraint. Fault detection filter is designed for a flight control system and the effectiveness is verified by the simulation results.

scholarly journals OPTIMIZATION OF PIECEWISE NON-LINEAR MULTI CONSTRAINED ECONOMIC POWER DISPATCH PROBLEM USING AN IMPROVED GENETIC ALGORITHM

2010 ◽  
pp. 320-326
Author(s):  
B. Padmanabhan ◽  
R. S. SivaKumar ◽  
J. Jasper
Keyword(s):  
Genetic Algorithm ◽  
Power Systems ◽  
Optimal Solution ◽  
Inequality Constraints ◽  
Local Optimum ◽  
Improved Genetic Algorithm ◽  
Non Linear ◽  
Equality And Inequality Constraints ◽  
Loading Effects ◽  
Economic Power Dispatch

In this paper, a more realistic formulation of the Economic Dispatch problem is proposed, which considers practical constraints and non linear characteristics. The proposed ED formulation includes ramp rate limits, valve loading effects, equality and inequality constraints, which usually are found simultaneously in realistic power systems. This paper presents a novel Genetic Algorithm to solve the economic load dispatch (ELD) problem of thermal generators of a power system. This method provides an almost global optimal solution, since they don’t get stuck at local optimum. The proposed method and its variants are validated for the two test systems consisting of 3 and 10 thermal units whose incremental fuel cost functions takes into account the valve-point loading effects.

scholarly journals Simultaneous Disturbance Compensation and H1/H∞ Optimization In Fault Detection Of UAVs

2018 ◽  
Vol 28 (2) ◽  
pp. 349-362 ◽  
Author(s):  
Hai Liu ◽  
Maiying Zhong ◽  
Rui Yang
Keyword(s):  
Fault Detection ◽  
Flight Control ◽  
Disturbance Compensation ◽  
Flight Control System ◽  
Multiple Sources ◽  
Multiple Disturbances ◽  
Robust Fault Detection ◽  
Modeling Errors ◽  
Time Varying Systems ◽  
Aerial Vehicle

Abstract This paper deals with the problem of robust fault detection (FD) for an unmanned aerial vehicle (UAV) flight control system (FCS). A nonlinear model to describe the UAV longitudinal motions is introduced, in which multiple sources of disturbances include wind effects, modeling errors and sensor noises are classified into groups. Then the FD problem is formulated as fault detection filter (FDF) design for a kind of nonlinear discrete time varying systems subject to multiple disturbances. In order to achieve robust FD performance against multiple disturbances, simultaneous disturbance compensation and H1/H∞ optimization are carried out in designing the FDF. The optimality of the proposed FDF is shown in detail. Finally, both simulations and real flight data are applied to validate the proposed method. An improvement of FD performance is achieved compared with the conventional H1/H∞-FDF.

Sign in / Sign up

Export Citation Format

Share Document