Design of FDI filter for an aircraft control system

István Szászi, Balázs Kulcsár, Gary J. Balas, József Bokor

Research output: Chapter in Book/Report/Conference proceedingChapter

19 Citations (Scopus)

Abstract

This paper presents a fault detection and isolation (FDI) filter design to linearized longitudinal dynamics of a Boeing 747 series 100/200. The FDI filter design based on geometric approach which relies on the use of (C, A) invariant subspaces and provides conditions on separability and mutual detectability of the failures. In our case the fault detection filter is sensitive to elevator fault and pitch rate sensor fault. Typically, the FDI filter design approach is elaborated for open loop model and it is applied in the closed loop. The robustness aspect of FDI will be considered and the effect of closing the loop is shown in nominal case as well as in uncertain case. In this paper the FDI filter designed for aircraft control system will be analyzed for a nominal closed loop system in the presence of sensor noise.

Original languageEnglish
Title of host publicationProceedings of the American Control Conference
Pages4232-4237
Number of pages6
Volume5
DOIs
Publication statusPublished - Jan 1 2002

Keywords

  • Aircraft control
  • Fault handling

ASJC Scopus subject areas

  • Electrical and Electronic Engineering

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  • Cite this

    Szászi, I., Kulcsár, B., Balas, G. J., & Bokor, J. (2002). Design of FDI filter for an aircraft control system. In Proceedings of the American Control Conference (Vol. 5, pp. 4232-4237) https://doi.org/10.1109/ACC.2002.1024596