Robust Control and Fault Detection Filter Design for Aircraft Pitch Axis

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.