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.

scholarly journals Application of Residual-Based EWMA Control Charts for Detecting Faults in Variable-Air-Volume Air Handling Unit System

2016 ◽  
Vol 2016 ◽  
pp. 1-7 ◽  
Author(s):  
Haitao Wang
Keyword(s):  
Time Series ◽  
Fault Detection ◽  
Control Chart ◽  
Detection Method ◽  
Time Data ◽  
Air Handling Unit ◽  
Ewma Control Chart ◽  
Robust Fault Detection ◽  
Modeling Errors ◽  
Control Limits

An online robust fault detection method is presented in this paper for VAV air handling unit and its implementation. Residual-based EWMA control chart is used to monitor the control processes of air handling unit and detect faults of air handling unit. In order to provide a level of robustness with respect to modeling errors, control limits are determined by incorporating time series model uncertainty in EWMA control chart. The fault detection method proposed was tested and validated using real time data collected from real VAV air-conditioning systems involving multiple artificial faults. The results of validation show residual-based EWMA control chart with designing control limits can improve the accuracy of fault detection through eliminating the negative effects of dynamic characteristics, serial correlation, normal transient changes of system, and time series modeling errors. The robust fault detection method proposed can provide an effective tool for detecting the faults of air handling units.

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.

scholarly journals Robust Fault Tolerant Control for a Class of Time-Delay Systems with Multiple Disturbances

2013 ◽  
Vol 2013 ◽  
pp. 1-8
Author(s):  
Songyin Cao ◽  
Jianzhong Qiao
Keyword(s):  
Time Delay ◽  
Flight Control ◽  
Disturbance Rejection ◽  
Fault Tolerant ◽  
Fault Tolerant Control ◽  
Delay Systems ◽  
Actuator Faults ◽  
Flight Control System ◽  
Multiple Disturbances ◽  
Fault Accommodation

A robust fault tolerant control (FTC) approach is addressed for a class of nonlinear systems with time delay, actuator faults, and multiple disturbances. The first part of the multiple disturbances is supposed to be an uncertain modeled disturbance and the second one represents a norm-bounded variable. First, a composite observer is designed to estimate the uncertain modeled disturbance and actuator fault simultaneously. Then, an FTC strategy consisting of disturbance observer based control (DOBC), fault accommodation, and a mixedH2/H∞controller is constructed to reconfigure the considered systems with disturbance rejection and attenuation performance. Finally, simulations for a flight control system are given to show the efficiency of the proposed approach.

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.

scholarly journals Design and Implementation of Communication Scheme between Ethernet and Multi-Serial Port

2018 ◽  
Vol 220 ◽  
pp. 10003
Author(s):  
Xin He ◽  
Jia’nan Wu ◽  
Hongde Deng ◽  
Zean Zhen ◽  
Chenyang Liu
Keyword(s):  
Flight Control ◽  
Physical Simulation ◽  
Serial Port ◽  
Flight Control System ◽  
Paper Briefly ◽  
Aerospace Technology ◽  
Communication Scheme ◽  
Time Requirements ◽  
Aerial Vehicle ◽  
Ethernet Controller

With the development of aerospace technology, the flight control system is getting more and more important for a UAV (Unmanned Aerial Vehicle) flying safely and efficiently. For collecting the experimental data without delay, this paper briefly reviews the design of the communication scheme, and provides the implemented results. Through using the controller LPC1768 to expand the serial port, and the Ethernet controller DP83848 to complete the communication by UDP protocol, it turns out that this method is able to reach the real-time requirements of the UAV semi-physical simulation.

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