Residual Generator Computation for Fault Detection of a General Aviation Aircraft

Bonfè, Marcello; Csataldi, P.; Geri, Walter; Simani, Silvio

doi:10.1016/s1474-6670(17)32288-7

Cited by 4 publications

(3 citation statements)

References 5 publications

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“…The pole location influences the transient dynamics of the designed residual filters, while the steady-state properties depend on the PM residual design, as it maximises the residual steady-state values with respect to step faults affecting input and output sensors. The poles of the residual functions could be optimised with respect to both fault and disturbance terms, as shown, for example, in a work by the same authors [17].…”

Section: Pm Residual Designmentioning

confidence: 99%

Design and Analysis of Robust Fault Diagnosis Schemes for a Simulated Aircraft Model

Benini

Bonfè

Castaldi

et al. 2008

Journal of Control Science and Engineering

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Several procedures for sensor fault detection and isolation (FDI) applied to a simulated model of a commercial aircraft are presented. The main contributions of the paper are related to the design and the optimisation of two FDI schemes based on a linear polynomial method (PM) and the nonlinear geometric approach (NLGA). The FDI strategies are applied to the aircraft model, characterised by tight-coupled longitudinal and lateral dynamics. The robustness and the reliability properties of the residual generators related to the considered FDI techniques are investigated and verified by simulating a general aircraft reference trajectory. Extensive simulations exploiting the Monte Carlo analysis tool are also used for assessing the overall performance capabilities of the developed FDI schemes, in the presence of turbulence, measurement, and model errors. Comparisons with other disturbance-decoupling methods for FDI based on neural networks (NNs) and unknown input kalman filter (UIKF) are finally reported.

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Section: Pm Residual Designmentioning

confidence: 99%

Design and Analysis of Robust Fault Diagnosis Schemes for a Simulated Aircraft Model

Benini

Bonfè

Castaldi

et al. 2008

Journal of Control Science and Engineering

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“…The adopted model has the relevant advantage of being explicitable, and hence suitable of a state space representation. The parameters in the analytic representation of the aerodynamic actions have been obtained from wind tunnel experimental data of a Piper PA30 [7], and the aerodynamic actions are expressed along the axes of the wind reference system. The non-linear attitude model is given by following relations by using the nomenclature introduced at the beginning:…”

Section: Aircraft Model Descriptionmentioning

confidence: 99%

“…Table (III) finally collects the minimal detectable and isolable fault amplitudes ρ on the aircraft actuators, when a simple geometric analysis (with respect to the fixed thresholds) of the residual signals r(t) has been performed with reference to the considered fault cases. Moreover, Table (III) reports and compares also the minimal detectable faults presented in a previous study [7] when the input and output aircraft measurements were assumed noise-free.…”

Section: Application Examplementioning

confidence: 99%

Modelling and identification of residual generator functions for fault detection and isolation of a small aircraft

Simani

Bonfè

2004

2004 43rd IEEE Conference on Decision and Control (CDC) (IEEE Cat. No.04CH37601)

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This paper addresses the design of a fault diagnosis scheme based on linear system frequency domain design. The main innovation of the method consists of integrating in one-step only, the derivation of an analytical model of residual generator functions for the diagnosis of the monitored process with the optimal design of the diagnostic system itself. Special attention will be given to the computation of residual generator functions in order to realise a complete fault diagnosis scheme when additive faults are present, as well as the optimisation of the performance that can be achieved under the presence of disturbance and unknown inputs. The combined modelling and identification approach for the computation of residual generators is exploited for fault detection and isolation of a small aircraft, characterised by a non-linear model, in the presence of disturbance. The results obtained in the simulation of the faulty behaviour of a Piper PA30 are finally reported.

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Design and Performance Analysis of Residual Generators for the Fdi of Aircraft Model Sensors

Simani

Bonfè

Castaldi

et al. 2007

IFAC Proceedings Volumes

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Residual Generator Computation for Fault Detection of a General Aviation Aircraft

Cited by 4 publications

References 5 publications

Design and Analysis of Robust Fault Diagnosis Schemes for a Simulated Aircraft Model

Design and Analysis of Robust Fault Diagnosis Schemes for a Simulated Aircraft Model

Modelling and identification of residual generator functions for fault detection and isolation of a small aircraft

Design and Performance Analysis of Residual Generators for the Fdi of Aircraft Model Sensors

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