Actuator fault estimation scheme for flight applications

Jiong Sang Yee; Jian Liang Wang; Bin Jiang

doi:10.1115/1.1515331

Actuator fault estimation scheme for flight applications

Jiong Sang Yee, Jian Liang Wang, Bin Jiang

Research output: Journal Publication › Article › peer-review

8 Citations (Scopus)

Abstract

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 _x 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 con-ditions.

Original language	English
Pages (from-to)	701-704
Number of pages	4
Journal	Journal of Dynamic Systems, Measurement and Control
Volume	124
Issue number	4
DOIs	https://doi.org/10.1115/1.1515331
Publication status	Published - Dec 2002
Externally published	Yes

ASJC Scopus subject areas

Control and Systems Engineering
Information Systems
Instrumentation
Mechanical Engineering
Computer Science Applications

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Cite this

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abstract = "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 x 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 con-ditions.",

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AB - 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 x 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 con-ditions.

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Actuator fault estimation scheme for flight applications

Abstract

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