Fault detection of electrical flight control system actuators using parameter dependent estimation

Vanek, Bálint; Szabó, Zoltán; Edelmayer, András; Bokor, József

doi:10.3182/20120829-3-mx-2028.00218

Cited by 10 publications

(13 citation statements)

References 12 publications

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“…The work described in [31,32,33,34,35,28] are examples of other approaches to actuator jam/runaway failure detection within ADDSAFE. The work in [31,34] uses a mathematical model of the actuator to design the FDD scheme and therefore requires a low order observer scheme.…”

Section: Actuator Jam/runaway Benchmark Problemmentioning

confidence: 99%

Second order sliding mode observers for the ADDSAFE actuator benchmark problem

Alwi

Edwards

2014

Control Engineering Practice

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This paper presents the evaluation process and results associated with two different fault detection and diagnosis (FDD) schemes applied to two different aircraft actuator fault benchmark problems. Although the schemes are different and bespoke for the problem being addressed, both are based on the concept of a second order sliding mode. Furthermore both designs are considered as 'local' in the sense that a localized actuator model is used together with local sensor measurements. The schemes do not involve the global aircraft equations of motion, and therefore have low order. The first FDD scheme is associated with the detection of oscillatory failure cases (OFC), while the second scheme is aimed at the detection of actuator jams/runaways. For the OFC benchmark problem, the idea is to estimate the OFC using a mathematical model of the actuator in which the rod speed is estimated using an adaptive second order exact differentiator. For the jam/runaway actuator benchmark problem, a more classical sliding mode observer based FDD scheme is considered in which the fault reconstruction is obtained from the equivalent output error injection signals associated with a second order sliding mode structure. The results presented in this paper summarize the design process from tuning, testing and finally industrial evaluation as part of the ADDSAFE project.

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Section: Actuator Jam/runaway Benchmark Problemmentioning

confidence: 99%

Second order sliding mode observers for the ADDSAFE actuator benchmark problem

Alwi

Edwards

2014

Control Engineering Practice

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“…Robustness of the FDI algorithm is determined by its capability to decouple the filter performance outputs from disturbances, errors, and unmodelled dynamics. In the present paper the fault detection filter is not designed, only a simplified representation is adopted based on the results from elevator FDI on commercial aircraft [27]. It has an approximate dynamics of G F DI =…”

Section: Fault Detectionmentioning

confidence: 99%

Supervisory fault tolerant control of the GTM UAV using LPV methods

Péni

Vanek

Szabó

et al. 2013

2013 Conference on Control and Fault-Tolerant Systems (SysTol)

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Abstract-The aim of the paper is to present a supervisory decentralized architecture for the design and development of reconfigurable and fault-tolerant control systems in aerial vehicles. The performance specifications with respect to flight envelope and fault states are guaranteed by local controllers, while the coordination of these components is provided by a supervisor. The monitoring components and FDI filters provide the supervisor with information about different fault operations, based on that it is able to make decisions about necessary interventions into the vehicle motions and guarantee reconfigurable and fault-tolerant operation of the aircraft. The design of the proposed reconfigurable and fault-tolerant control is based on an LPV method that uses monitored scheduling variables during the operation of the vehicle. The design is demonstrated on the high-fidelity simulation model of the NASA AirSTAR Flight Test Vehicle.

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“…The importance of this paper is on the comparison of the global (aircraft level) and local (component level) methods with respect to their detection performance, development complexity and implementation aspects. An aileron fault detection case is handled by a geometric FDI filter (Vanek, Szabó, Edelmayer, & Bokor, 2011) using an aircraft level mathematical model, while the elevator fault detection is tackled by a more conventional detection filter based approach (Vanek, Szabó, Edelmayer, & Bokor, 2012) using the local mathematical description of the hydraulic actuator.…”

Section: Introductionmentioning

confidence: 99%

Bridging the gap between theory and practice in LPV fault detection for flight control actuators

Vanek¹,

Edelmayer²,

Szabó³

et al. 2014

Control Engineering Practice

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a b s t r a c tTwo different approaches for fault detection, the geometric and the detection filter based methods, are compared in the paper from practical aspects, using the linear parameter-varying (LPV) framework. Presenting two designs allows a comparison of global, system level, and local component level fault detection methods with special emphasis on their relevance to aircraft industry. Practical engineering design decisions are highlighted via applying them to a high-fidelity commercial aircraft problem. The successive steps of the design, including fault modeling, LPV model generation, and LPV FDI filter synthesis, including implementation aspects, are discussed. Results are presented according to the industrial assessment perspectives phrased within the EU ADDSAFE project.

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Fault detection of electrical flight control system actuators using parameter dependent estimation

Cited by 10 publications

References 12 publications

Second order sliding mode observers for the ADDSAFE actuator benchmark problem

Second order sliding mode observers for the ADDSAFE actuator benchmark problem

Supervisory fault tolerant control of the GTM UAV using LPV methods

Bridging the gap between theory and practice in LPV fault detection for flight control actuators

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