False alarm mechanism and control of aircraft hydraulic system

Author

Guishuang Tian ; Shaoping Wang ; Zhaomin He

Author_Institution

Sci. & Technol. on Aircraft Control Lab., Beihang Univ., Beijing, China

fYear

2013

fDate

19-21 June 2013

Firstpage

1565

Lastpage

1568

Abstract

Built-in-Test (BIT) is widely used in aircraft to improve the system´s reliability and safety. However, the false alarm of BIT makes it difficult to practical. After investigating the mechanism of false alarm of BIT from sensor failure, signal coupling, unreasonable threshold and uncertainty of fault decision method, an improved fault diagnosis method integrated with sensor redundancy configuration, delay decision and dynamic threshold is proposed. The result from the ground simulation platform indicates the method´s effectiveness.

Keywords

aerospace safety; aerospace testing; aircraft control; built-in self test; fault diagnosis; hydraulic systems; reliability; sensors; uncertain systems; vehicle dynamics; BIT false alarm mechanism; aircraft hydraulic system control; built-in-test; delay decision; dynamic threshold; fault decision method uncertainty; improved fault diagnosis method; sensor failure; sensor redundancy configuration; signal coupling; system reliability improvement; system safety improvement; unreasonable threshold; Aerospace control; Aircraft; Atmospheric modeling; Delays; Fault diagnosis; Hydraulic systems; Safety; aircraft hydraulic System; built-in-test; false Alarm control;

fLanguage

English

Publisher

ieee

Conference_Titel

Industrial Electronics and Applications (ICIEA), 2013 8th IEEE Conference on

Conference_Location

Melbourne, VIC

Print_ISBN

978-1-4673-6320-4

Type

conf

DOI

10.1109/ICIEA.2013.6566617

Filename

6566617