Fault detection and isolation for on‐board sensors of a general aviation aircraft

Bonfè, Marcello; Castaldi, Paolo; Geri, Walter; Simani, Silvio

doi:10.1002/acs.906

Cited by 41 publications

(23 citation statements)

References 31 publications

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“…Similar considerations can be applied to design a bank of residual generators to univocally isolate a fault concerning one of the output sensors. More design details can be found in [11].…”

Section: R(s) R(t) = Sy(s) Y(t) + Sc(s) C(t)mentioning

confidence: 99%

“…The polynomial R(s) can be arbitrarily selected, even if the choice of R(s) has a direct influence on the properties of the filter [11] .…”

Section: R(s) R(t) = Sy(s) Y(t) + Sc(s) C(t)mentioning

confidence: 99%

“…In [11], instead, the design of residual generators based on the NLGA with respect to just the longitudinal dynamics (3DOF aircraft model) of a general aviation aircraft can be found. Even though both the present work and [10,11] have a common framework, the present paper provides a generalisation to an aircraft model based on a 6 degrees of freedom (6 DOF) rigid body formulation and the aim is to carry out the FDI even if the flight conditions are not compliant with the hypothesis of decoupled longitudinal and lateral-directional dynamics. Moreover, the NLGA residual generators have been designed in order to be analytically decoupled from the vertical and lateral components of the wind (gusts and turbulence).…”

Section: Introductionmentioning

confidence: 99%

“…The simulation model, detailed in [11], is made up of a 6DOF rigid body structure as well as the models of wind gusts, Dryden atmospheric turbulence, measurement sensors, servo actuators and a classical autopilot.…”

Section: Introductionmentioning

confidence: 99%

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Design and performance evaluation of residual genertors for the FDI of an aircraft

Bonfè

Castaldi

Geri

et al. 2007

Int J Automat Comput

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In this work, several procedures for the fault detection and isolation (FDI) on general aviation aircraft sensors are presented. In order to provide a comprehensive wide-spectrum treatment, both linear and nonlinear, model-based and data-driven methodologies are considered. The main contributions of the paper are related to the development of both FDI polynomial method (PM) and FDI scheme based on the nonLinear geometric approach (NLGA). As to the PM, the obtained results highlight a good trade-off between solution complexity and resulting performances. Moreover, the proposed PM is especially useful when robust solutions are required for minimising the effects of modelling errors and noise, while maximising fault sensitivity. As to the NLGA, the proposed work is the first development and robust application of the NLGA to an aircraft model in flight conditions characterised by tight-coupled longitudinal and lateral dynamics. In order to verify the robustness of the residual generators related to the previous FDI techniques, the simulation results adopt a typical aircraft reference trajectory embedding several steady-state flight conditions, such as straight flight phases and coordinated turns. Moreover, the simulations are performed in the presence of both measurement and modelling errors. Finally, extensive simulations are used for assessing the overall capabilities of the developed FDI schemes and a comparison with neural networks (NN) and unknown input Kalman filter (UIKF) diagnosis methods is performed.

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“…Similar considerations can be applied to design a bank of residual generators to univocally isolate a fault concerning one of the output sensors. More design details can be found in [11].…”

Section: R(s) R(t) = Sy(s) Y(t) + Sc(s) C(t)mentioning

confidence: 99%

“…The polynomial R(s) can be arbitrarily selected, even if the choice of R(s) has a direct influence on the properties of the filter [11] .…”

Section: R(s) R(t) = Sy(s) Y(t) + Sc(s) C(t)mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Design and performance evaluation of residual genertors for the FDI of an aircraft

Bonfè

Castaldi

Geri

et al. 2007

Int J Automat Comput

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“…• There exists a proper scalar componentx 1s of the state vectorx 1 such that the corresponding scalar component of the output vector isȳ 1s =x 1s and the following relation holds (Bonfè et al, 2007):…”

mentioning

confidence: 99%

Active fault tolerant control of nonlinear systems: The cart-pole example

Bonfè¹,

Castaldi²,

Mimmo³

et al. 2011

International Journal of Applied Mathematics and Computer Science

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This paper describes the design of fault diagnosis and active fault tolerant control schemes that can be developed for nonlinear systems. The methodology is based on a fault detection and diagnosis procedure relying on adaptive filters designed via the nonlinear geometric approach, which allows obtaining the disturbance de-coupling property. The controller reconfiguration exploits directly the on-line estimate of the fault signal. The classical model of an inverted pendulum on a cart is considered as an application example, in order to highlight the complete design procedure, including the mathematical aspects of the nonlinear disturbance de-coupling method based on the nonlinear differential geometry, as well as the feasibility and efficiency of the proposed approach. Extensive simulations of the benchmark process and Monte Carlo analysis are practical tools for assessing experimentally the robustness and stability properties of the developed fault tolerant control scheme, in the presence of modelling and measurement errors. The fault tolerant control method is also compared with a different approach relying on sliding mode control, in order to evaluate benefits and drawbacks of both techniques. This comparison highlights that the proposed design methodology can constitute a reliable and robust approach for application to real nonlinear processes.

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Nonlinear Methods for Fault Diagnosis

Simani

Castaldi

2021

Diagnosis and Fault‐tolerant Control 2

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Fault detection and isolation for on‐board sensors of a general aviation aircraft

Cited by 41 publications

References 31 publications

Design and performance evaluation of residual genertors for the FDI of an aircraft

Design and performance evaluation of residual genertors for the FDI of an aircraft

Active fault tolerant control of nonlinear systems: The cart-pole example

Nonlinear Methods for Fault Diagnosis

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