Detection and Isolation of Actuator/Surface Faults for a Large Transport Aircraft

Varga, Andras

doi:10.1007/978-3-642-11690-2_15

Cited by 12 publications

(9 citation statements)

References 21 publications

(34 reference statements)

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“…Earlier studies investigated how dynamic and semi-static models could be used for diagnosis of control surface faults on this family of aircraft (Hansen and Blanke, 2012) and the issue has been dealt with for large aircraft with hydraulic actuators in (Varga, 2010). For small aircraft with uncertain or lacking model information, an adaptive and very simple model of this relationship was found useful .…”

Section: Control Surface or Actuator Defectmentioning

confidence: 99%

A Framework for Diagnosis of Critical Faults in Unmanned Aerial Vehicles

Hansen

Blanke

Adrian³

2014

IFAC Proceedings Volumes

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Unmanned Aerial Vehicles (UAVs) need a large degree of tolerance towards faults.If not diagnosed and handled in time, many types of faults can have catastrophic consequences if they occur during flight. Prognosis of faults is also valuable and so is the ability to distinguish the severity of the different faults in terms of both consequences and the frequency with which they appear. In this paper flight data from a fleet of UAVs is analysed with respect to certain faults and their frequency of appearance. Data is taken from a group of UAV's of the same type but with small differences in weight and handling due to different types of payloads and engines used. Categories of critical faults, that could and have caused UAV crashes are analysed and requirements to diagnosis are formulated. Faults in air system sensors and in control surfaces are given special attention. In a stochastic framework, and based on a large number of data logged during flights, diagnostic methods are employed to diagnose faults and the performance of these fault detectors are evaluated against flight data. The paper demonstrates a significant potential for reducing the risk of unplanned loss of remotely piloted vehicles used by the Danish Navy for target practice.

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Section: Control Surface or Actuator Defectmentioning

confidence: 99%

A Framework for Diagnosis of Critical Faults in Unmanned Aerial Vehicles

Hansen

Blanke

Adrian³

2014

IFAC Proceedings Volumes

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“…Assume that the actuator/surface FDI problem is solved through one of the existing methods in literature . It is required to design TSKF for state vector estimation and actuator/surface fault identification.…”

Section: Design Of Two‐stage Kalman Filter For State Vector Estimatiomentioning

confidence: 99%

“…The proposed method requires the FDI block for realization. It is assumed that a single actuator is chosen via one of the existing methods in literature .…”

Section: Design Of Two‐stage Kalman Filter For State Vector Estimatiomentioning

confidence: 99%

“…A potential problem arises when the actuator is fault free, but the corresponding control surface is damaged. The associated loss of effectiveness of the actuation/control surface system cannot be detected in this way . In practice, it can meet certain surface faults, for instance, partial loss of a control surface (when a part of the control surface breaks off), deformation of the control surface, and control surface icing, that cause the different control effectiveness factors for the actuator.…”

Section: Introductionmentioning

confidence: 99%

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Two-stage Kalman filter-based actuator/surface fault identification and reconfigurable control applied to F-16 fighter dynamics

Hajiyev

2012

Int. J. Adapt. Control Signal Process.

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In this study, an active fault-tolerant control technique with reconfiguration against actuator/surface failures is presented. A two-stage Kalman filter is designed in order to identify the control distribution matrix elements that correspond to the faulty actuator/surface; thus, the control reconfiguration is carried out using this identified control distribution matrix. The actuator/surface fault identification problem is solved through two jointly operating Kalman filters: the first one is for the estimation of the control distribution matrix elements that correspond to the faulty actuator/surface, and the second one is for the estimation of the state variables of the aircraft model.A structure for the active fault-tolerant aircraft flight control system with reconfiguration against actuator/surface failures is presented. A control reconfiguration action is taken in order to keep the performance of the impaired aircraft the same as that of the unimpaired aircraft.In simulations, the nonlinear flight dynamics of an AFTI/F-16 fighter model is considered, and the performance of the proposed actuator/surface failure identification and reconfigurable control schemes are examined for this model.The active fault-tolerant control systems consist of two basic subsystems [9]:1. fault detection and isolation (FDI) or system identification and 2. control reconfiguration or restructure.In an active fault-tolerant control system, faults are detected and identified by an FDI scheme, and the controllers are reconfigured accordingly online in real time. An effective FDI procedure is critical for designing high-performance active fault-tolerant control systems. Many model-based FDI techniques have been developed to detect and identify the sensor and actuator faults via the analytical redundancy, state estimation, and parameter identification approaches [7,[10][11][12][13][14][15][16][17][18][19][20][21][22][23][24][25].The works [26-28] address the control allocation problem for a nonlinear over-actuated timevarying system where parameters affine in the actuator model may be assumed unknown. In order to cope with an unknown parameter vector in the actuator model, an adaptive law is defined. The parameter estimate is used in the control allocation algorithm, and a certainty equivalent adaptive optimal control allocation can be defined. But these works do not mention FDI techniques.Under the assumption that system faults can be detected, isolated, and identified via FDI techniques, several reconfigurable control methods have been developed in the literature. Existing reconfigurable controller design methods are based on one of the following approaches: linear quadratic regulator (LQR) [5,29], model following [30,31], adaptive control [32,33], pseudoinverse [17,34,35], multiple model [32,[36][37][38][39], eigenstructure assignment [6,40,41], model predictive control [42], and neural networks [43][44][45]. However, most methods assume that a perfect post-fault model of the system is known and the post-fault system model is not know...

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“…13,[26][27][28][29] This holds also for related FDI work. 30,31 A book about the work and results of GARTEUR FM-AG(16) is in preparation for publication in the Lecture Notes in Control and Information Sciences series by Springer-Verlag.…”

Section: 25mentioning

confidence: 99%

Piloted Simulator Evaluation Results of New Fault-Tolerant Flight Control Algorithm

Lombaerts

Smaili

Stroosma

et al. 2009

Journal of Guidance, Control, and Dynamics

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A high fidelity aircraft simulation model, reconstructed using the Digital Flight Data Recorder (DFDR) of the 1992 Amsterdam Bijlmermeer aircraft accident (Flight 1862), has been used to evaluate a new Fault-Tolerant Flight Control Algorithm in an online piloted evaluation. This paper focuses on the piloted simulator evaluation results. Reconfiguring control is implemented by making use of Adaptive Nonlinear Dynamic Inversion (ANDI) for manual fly by wire control. After discussing the modular adaptive controller setup, the experiment is described for a piloted simulator evaluation of this innovative reconfigurable control algorithm applied to a damaged civil transport aircraft. The evaluation scenario, measurements and experimental design, as well as the real-time implementation are described. Finally, reconfiguration test results are shown for damaged aircraft models including component as well as structural failures. The evaluation shows that the FTFC algorithm is able to restore conventional control strategies after the aircraft configuration has changed dramatically due to these severe failures. The algorithm supports the pilot after a failure by lowering workload and allowing a safe return to the airport. For most failures, the handling qualities are shown to degrade less with a failure than the baseline classical control system does.

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Detection and Isolation of Actuator/Surface Faults for a Large Transport Aircraft

Cited by 12 publications

References 21 publications

A Framework for Diagnosis of Critical Faults in Unmanned Aerial Vehicles

A Framework for Diagnosis of Critical Faults in Unmanned Aerial Vehicles

Two-stage Kalman filter-based actuator/surface fault identification and reconfigurable control applied to F-16 fighter dynamics

Piloted Simulator Evaluation Results of New Fault-Tolerant Flight Control Algorithm

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