Discrete-time actuator fault estimation design for flight control application

2004 ◽  
Author(s):  
Jiong-Sang Yee ◽  
Bin Jiang ◽  
Jian Liang Wang ◽  
Yan Li
Keyword(s):  
Discrete Time ◽  
Flight Control ◽  
Fault Estimation ◽  
Actuator Fault ◽  
Control Application

Joint interval state and actuator fault estimation for linear discrete-time delayed systems

2021 ◽  
Author(s):  
Naima Sehli ◽  
Kaouther Ibn Taarit ◽  
Zhenhua Wang ◽  
Tarek Raissi ◽  
Moufida Ksouri
Keyword(s):  
Discrete Time ◽  
Fault Estimation ◽  
Actuator Fault ◽  
Delayed Systems

Actuator Fault Estimation Based on Proportional Integral Observer for Discrete-Time Switched Systems

2018 ◽  
Vol 141 (3) ◽  
Author(s):  
Abdellah Benzaouia ◽  
Kenza Telbissi
Keyword(s):  
Discrete Time ◽  
Switched Systems ◽  
Sufficient Conditions ◽  
Fault Estimation ◽  
Linear Matrix ◽  
Actuator Fault ◽  
New Approach ◽  
Unknown Disturbance ◽  
Multiple Lyapunov Functional ◽  
Fault Information

This paper presents a new approach of actuator fault estimation (FE) for discrete-time switched systems against unknown disturbance. The proposed FE approach uses a new switching observer methodology, which allows to obtain fast and exact fault information. Sufficient conditions are achieved by using multiple Lyapunov functional. These conditions are manipulated in a simple way in order to obtain a new linear matrix inequality (LMI) with slack variables and observer gains matrices. Finally, two illustrative examples are performed to prove the effectiveness of the proposed method.

Actuator Fault Estimation Scheme for Flight Applications

2002 ◽  
Vol 124 (4) ◽  
pp. 701-704 ◽  
Author(s):  
Jiong-Sang Yee ◽  
Jian Liang Wang ◽  
Bin Jiang
Keyword(s):  
Flight Control ◽  
Fault Tolerant ◽  
Fault Estimation ◽  
Actuator Fault ◽  
Flight Control System ◽  
Fighter Aircraft ◽  
Flying Qualities ◽  
Estimation Scheme ◽  
On Line ◽  
Loss Of Actuator Effectiveness

The paper presents a new actuator fault estimation scheme based on the augmented error method that estimates the actuator effectiveness on-line. The proposed scheme is applied to a fault-tolerant flight control system design for an F4-E fighter aircraft. The output of a nominal H∞ controller is continuously reconfigured to compensate for any loss of actuator effectiveness. Simulation results demonstrate good fault estimation and flying qualities obtained using the proposed scheme under the actuator fault conditions.

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