Design of Residual Generators for the Fault Diagnosis of General Aviation Aircraft.

This paper addresses the problem of the diagnosis of the input sensor faults on general aviation aircraft, characterised by a non–linear model, in the presence of windgust disturbance and measurement errors. In particular, this work investigates the design of residual generators in order to realise complete diagnosis schemes when additive faults are present. The use of an input–output description for the linearised model of the aircraft allows to compute in a straightforward way the residual generators for fault diagnosis. These tools lead to dynamic filters that can achieve both good disturbance signal decoupling and robustness properties with respect to both linearisation error and measurement noise. Mathematical descriptions of theaircraftmeasurementsensorsarealsotakenintoaccount. The results obtained in the simulation of the faulty behaviour of a PIPER PA30 aircraft are finally reported.