Actuator Fault Diagnosis for Flight Control System Based on Sliding Mode Observer

被引：0

作者：

Quan, Lu ^{[1
]}

Jiang, Bin ^{[1
]}

Yang, Pu ^{[1
]}

机构：

[1] Nanjing Univ Aeronaut & Astronaut, Coll Automat Engn, Nanjing 210016, Peoples R China

来源：

PROCEEDINGS OF THE 30TH CHINESE CONTROL AND DECISION CONFERENCE (2018 CCDC) | 2018年

关键词：

Sliding mode observer; Fault diagnosis; Flight control system; DESIGN; STATE;

D O I：

暂无

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

In this paper, a sliding mode observer based fault diagnosis method was proposed for a class of linear systems with the disturbance and model uncertainty to detect the actuator faults. The difficulty on the sliding mode observer method can be directly solved by using linear matrix inequalities (LMIS). The stability of the designed sliding mode observer can be guaranteed by Lyapunov stability theory. The proposed actuator fault diagnosis method is tested in a 3-DOF aircraft simulation platform to illustrate the performance of the proposed observer and the effectiveness of the fault diagnosis algorithm.

引用

页码：3243 / 3247

页数：5

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