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.
|Title of host publication||Proceedings of the American Control Conference|
|Number of pages||6|
|Publication status||Published - Jan 1 2002|
- Aircraft control
- Fault handling
ASJC Scopus subject areas
- Electrical and Electronic Engineering