Actuator Fault Diagnosis in a Boeing 747 Model via Adaptive Modified Two-Stage Kalman Filter

被引：12

作者：

Caliskan, Fikret ^{[1
]}

Zhang, Youmin ^{[2
]}

Wu, N. Eva ^{[3
]}

Shin, Jong-Yeob ^{[4
]}

机构：

[1] Istanbul Tech Univ, Dept Control Engn, TR-34469 Istanbul, Turkey

[2] Concordia Univ, Dept Mech & Ind Engn, Montreal, PQ H3G 1M8, Canada

[3] SUNY Binghamton, Dept Elect & Comp Engn, Binghamton, NY 13902 USA

[4] Gulfstream Aerosp Corp, Savannah, GA 31402 USA

来源：

INTERNATIONAL JOURNAL OF AEROSPACE ENGINEERING | 2014年 / 2014卷

关键词：

FLIGHT CONTROL; TOLERANT CONTROL; ACCOMMODATION; SCHEME;

D O I：

10.1155/2014/472395

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

An adaptive modified two-stage linear Kalman filtering algorithm is utilized to identify the loss of control effectiveness and the magnitude of low degree of stuck faults in a closed-loop nonlinear B747 aircraft. Control effectiveness factors and stuck magnitudes are used to quantify faults entering control systems through actuators. Pseudorandom excitation inputs are used to help distinguish partial loss and stuck faults. The partial loss and stuck faults in the stabilizer are isolated and identified successfully.

引用

页数：10

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