This paper addresses the problem of the detection and isola!ion of actuator fauIts on a general aviation aircraft, characterised by a nonlinear model, in the presence of wind gust disturbances. 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 a canonical input-output polynomial description for the hearised model of the aircraft allows to compute in a straightforward way minimal order residual generators. These tools lead to dynamic filters that can guarantee both disturbance signal decoupling and robustness properties with respect to linehation errors. The results obtained in the simulation of the Faulty bebaviour of a Piper PA30 are aaUy reported.
S. Simani, M. Bonfè, P. Castaldi, W. Geri (2004). Residual Generator Function Design for Actuator Fault Detection and Isolation of a Piper PA 30 Aircraft. ATLANTIS, BAHAMAS : s.n.
Residual Generator Function Design for Actuator Fault Detection and Isolation of a Piper PA 30 Aircraft
CASTALDI, PAOLO;GERI, WALTER
2004
Abstract
This paper addresses the problem of the detection and isola!ion of actuator fauIts on a general aviation aircraft, characterised by a nonlinear model, in the presence of wind gust disturbances. 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 a canonical input-output polynomial description for the hearised model of the aircraft allows to compute in a straightforward way minimal order residual generators. These tools lead to dynamic filters that can guarantee both disturbance signal decoupling and robustness properties with respect to linehation errors. The results obtained in the simulation of the Faulty bebaviour of a Piper PA30 are aaUy reported.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
