'Periodica Polytechnica Budapest University of Technology and Economics'
Abstract
This paper presents a robust control and fault detection filter
design for linearized longitudinal dynamics of F-16 aircraft. The
control design is based on mu; synthesis method which guarantees
the robust performance requirements and takes the structured
uncertainty into consideration. In case of F-16 aircraft, it is
assumed that an elevator failure and a sensor failure occur
during the system operation. To ensure the safety of aircraft
control system a fault detection and isolation (FDI) filter is
designed. The fault detection filter design based on geometric
approach relies on the use of (C,A) invariant subspaces which
makes possible the decoupling of different types of failure.
Typically, the FDI filter design approach is elaborated for open
loop model and it is applied in the closed loop. In this paper the
FDI filter designed for aircraft control system will be analyzed
for a closed loop system