Detection and Isolation of Actuator/Surface Faults for a Large Transport Aircraft

Abstract

We consider the problem of designing residual generators with least dynamical orders to solve actuator fault detection and isolation problems for a Boeing 747-100/200 aircraft. The main result of our analysis is the proof of feasibility of the complete isolation of all primary actuator/surface faults in the nominal case by using a minimal number of additional surface angle sensors. The analysis of the nominal case provides residual filter specifications which can be employed in a more realistic design, where robustness aspects with respect to external noise (gusts, measurements) and parametric/flight condition uncertainties are also considered.