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Denis Efimov – One of the best experts on this subject based on the ideXlab platform.

  • A non-conservative $H_{-} / H_{\infty}$ solution for early and robust fault diagnosis in Aircraft Control surface servo-loops
    Control Engineering Practice, 2014
    Co-Authors: David Henry, Jérôme Cieslak, Ali Zolghadri, Denis Efimov

    Abstract:

    The presented work is undertaken within the FP7-ADDSAFE (Advanced Fault Diagnosis for Sustainable Flight Guidance and Control) project, a European collaborative project that aims to propose new fault diagnosis techniques for AIRBUS Aircraft that could significantly advance the Aircraft performance, e.g. by optimizing the Aircraft structural design (weight saving) or decreasing its environmental footprint (e.g. less fuel consumption and noise). The paper discusses the design of a model-based fault detection scheme for robust and early detection of faults in Aircraft Control surfaces servo-loop. The proposed strategy consists of two fault detectors: The first fault detector is based on a H- / H\infinity residual generator that maximizes sensitivity to any kind of Control surface servo-loop faults whilst simultaneously minimizes the influence of unknown inputs. The second fault detector consists of a pure H\infinity residual generator that is sensitive to a restricted set of faults and robust to unknown inputs. By such a structured strategy, it is shown that it is possible to discriminate between different fault types occurring in the Control surfaces servo-loop. Monte-Carlo campaigns from a highly representative simulator provided by AIRBUS as well as experimental results obtained on AIRBUS test facilities demonstrate the fault detection performance, robustness and viability of the proposed technique.

  • A non-conservative $H_{-} / H_{\infty}$ solution for early and robust fault diagnosis in Aircraft Control surface servo-loops
    Control Engineering Practice, 2014
    Co-Authors: David Henry, Jérôme Cieslak, Ali Zolghadri, Denis Efimov

    Abstract:

    The presented work is undertaken within the FP7-ADDSAFE (Advanced Fault Diagnosis for Sustainable Flight Guidance and Control) project, a European collaborative project that aims to propose new fault diagnosis techniques for AIRBUS Aircraft that could significantly advance the Aircraft performance, e.g. by optimizing the Aircraft structural design (weight saving) or decreasing its environmental footprint (e.g. less fuel consumption and noise). The paper discusses the design of a model-based fault detection scheme for robust and early detection of faults in Aircraft Control surfaces servo-loop. The proposed strategy consists of two fault detectors: The first fault detector is based on a H- / H\infinity residual generator that maximizes sensitivity to any kind of Control surface servo-loop faults whilst simultaneously minimizes the influence of unknown inputs. The second fault detector consists of a pure H\infinity residual generator that is sensitive to a restricted set of faults and robust to unknown inputs. By such a structured strategy, it is shown that it is possible to discriminate between different fault types occurring in the Control surfaces servo-loop. Monte-Carlo campaigns from a highly representative simulator provided by AIRBUS as well as experimental results obtained on AIRBUS test facilities demonstrate the fault detection performance, robustness and viability of the proposed technique.

  • A Method for Actuator Lock-in-place Failure Detection in Aircraft Control Surface Servo-loops
    , 2014
    Co-Authors: Jérôme Cieslak, Denis Efimov, Ali Zolghadri, Philippe Goupil, Anca Gheorghe, Rémy Dayre

    Abstract:

    This paper deals with a signal-based method for robust and early detection of lock-in-place failures (a.k.a. jamming) in Aircraft Control surface servo-loops. Earlier and robust detection of such failures is an important issue since they may cause additional structural load and affect the sustainability of civil transport airplane. The proposed signal-based scheme uses a sliding-mode differentiator to provide derivatives of measurable signals in noisy environment. Jamming events are next detected by using a dedicated decision making-rule that is able to detect actuator outage (the stuck value can be near zero). The proposed monitoring scheme has been tested on Airbus test facilities located at Toulouse, France. The results confirm good level of robustness and performance, even in extreme situations. The proposed technique can be applied, with slight modifications, to any type of actuator, e.g. Hydraulic, Electro-Hydrostatic (EHA) or Electro-Backup-Hydrostatic (EBHA) actuators.

Ali Zolghadri – One of the best experts on this subject based on the ideXlab platform.

  • Set-membership fault detection under noisy environment with application to the detection of abnormal Aircraft Control surface positions
    International Journal of Control, 2015
    Co-Authors: Rihab El Houda Thabet, Christophe Combastel, Tarek Raissi, Ali Zolghadri

    Abstract:

    The paper develops a set membership detection methodology which is applied to the detection of abnormal positions of Aircraft Control surfaces. Robust and early detection of such abnormal positions is an important issue for early system reconfiguration and overall optimization of Aircraft design. In order to improve fault sensitivity while ensuring a high level of robustness, the method combines a data-driven characterization of noise and a model-driven approach based on interval prediction. The efficiency of the proposed methodology is illustrated through simulation results obtained based on data recorded in several flight scenarios of a highly representative Aircraft benchmark.

  • A non-conservative $H_{-} / H_{\infty}$ solution for early and robust fault diagnosis in Aircraft Control surface servo-loops
    Control Engineering Practice, 2014
    Co-Authors: David Henry, Jérôme Cieslak, Ali Zolghadri, Denis Efimov

    Abstract:

    The presented work is undertaken within the FP7-ADDSAFE (Advanced Fault Diagnosis for Sustainable Flight Guidance and Control) project, a European collaborative project that aims to propose new fault diagnosis techniques for AIRBUS Aircraft that could significantly advance the Aircraft performance, e.g. by optimizing the Aircraft structural design (weight saving) or decreasing its environmental footprint (e.g. less fuel consumption and noise). The paper discusses the design of a model-based fault detection scheme for robust and early detection of faults in Aircraft Control surfaces servo-loop. The proposed strategy consists of two fault detectors: The first fault detector is based on a H- / H\infinity residual generator that maximizes sensitivity to any kind of Control surface servo-loop faults whilst simultaneously minimizes the influence of unknown inputs. The second fault detector consists of a pure H\infinity residual generator that is sensitive to a restricted set of faults and robust to unknown inputs. By such a structured strategy, it is shown that it is possible to discriminate between different fault types occurring in the Control surfaces servo-loop. Monte-Carlo campaigns from a highly representative simulator provided by AIRBUS as well as experimental results obtained on AIRBUS test facilities demonstrate the fault detection performance, robustness and viability of the proposed technique.

  • A non-conservative $H_{-} / H_{\infty}$ solution for early and robust fault diagnosis in Aircraft Control surface servo-loops
    Control Engineering Practice, 2014
    Co-Authors: David Henry, Jérôme Cieslak, Ali Zolghadri, Denis Efimov

    Abstract:

    The presented work is undertaken within the FP7-ADDSAFE (Advanced Fault Diagnosis for Sustainable Flight Guidance and Control) project, a European collaborative project that aims to propose new fault diagnosis techniques for AIRBUS Aircraft that could significantly advance the Aircraft performance, e.g. by optimizing the Aircraft structural design (weight saving) or decreasing its environmental footprint (e.g. less fuel consumption and noise). The paper discusses the design of a model-based fault detection scheme for robust and early detection of faults in Aircraft Control surfaces servo-loop. The proposed strategy consists of two fault detectors: The first fault detector is based on a H- / H\infinity residual generator that maximizes sensitivity to any kind of Control surface servo-loop faults whilst simultaneously minimizes the influence of unknown inputs. The second fault detector consists of a pure H\infinity residual generator that is sensitive to a restricted set of faults and robust to unknown inputs. By such a structured strategy, it is shown that it is possible to discriminate between different fault types occurring in the Control surfaces servo-loop. Monte-Carlo campaigns from a highly representative simulator provided by AIRBUS as well as experimental results obtained on AIRBUS test facilities demonstrate the fault detection performance, robustness and viability of the proposed technique.

David Henry – One of the best experts on this subject based on the ideXlab platform.

  • A non-conservative $H_{-} / H_{\infty}$ solution for early and robust fault diagnosis in Aircraft Control surface servo-loops
    Control Engineering Practice, 2014
    Co-Authors: David Henry, Jérôme Cieslak, Ali Zolghadri, Denis Efimov

    Abstract:

    The presented work is undertaken within the FP7-ADDSAFE (Advanced Fault Diagnosis for Sustainable Flight Guidance and Control) project, a European collaborative project that aims to propose new fault diagnosis techniques for AIRBUS Aircraft that could significantly advance the Aircraft performance, e.g. by optimizing the Aircraft structural design (weight saving) or decreasing its environmental footprint (e.g. less fuel consumption and noise). The paper discusses the design of a model-based fault detection scheme for robust and early detection of faults in Aircraft Control surfaces servo-loop. The proposed strategy consists of two fault detectors: The first fault detector is based on a H- / H\infinity residual generator that maximizes sensitivity to any kind of Control surface servo-loop faults whilst simultaneously minimizes the influence of unknown inputs. The second fault detector consists of a pure H\infinity residual generator that is sensitive to a restricted set of faults and robust to unknown inputs. By such a structured strategy, it is shown that it is possible to discriminate between different fault types occurring in the Control surfaces servo-loop. Monte-Carlo campaigns from a highly representative simulator provided by AIRBUS as well as experimental results obtained on AIRBUS test facilities demonstrate the fault detection performance, robustness and viability of the proposed technique.

  • A non-conservative $H_{-} / H_{\infty}$ solution for early and robust fault diagnosis in Aircraft Control surface servo-loops
    Control Engineering Practice, 2014
    Co-Authors: David Henry, Jérôme Cieslak, Ali Zolghadri, Denis Efimov

    Abstract:

    The presented work is undertaken within the FP7-ADDSAFE (Advanced Fault Diagnosis for Sustainable Flight Guidance and Control) project, a European collaborative project that aims to propose new fault diagnosis techniques for AIRBUS Aircraft that could significantly advance the Aircraft performance, e.g. by optimizing the Aircraft structural design (weight saving) or decreasing its environmental footprint (e.g. less fuel consumption and noise). The paper discusses the design of a model-based fault detection scheme for robust and early detection of faults in Aircraft Control surfaces servo-loop. The proposed strategy consists of two fault detectors: The first fault detector is based on a H- / H\infinity residual generator that maximizes sensitivity to any kind of Control surface servo-loop faults whilst simultaneously minimizes the influence of unknown inputs. The second fault detector consists of a pure H\infinity residual generator that is sensitive to a restricted set of faults and robust to unknown inputs. By such a structured strategy, it is shown that it is possible to discriminate between different fault types occurring in the Control surfaces servo-loop. Monte-Carlo campaigns from a highly representative simulator provided by AIRBUS as well as experimental results obtained on AIRBUS test facilities demonstrate the fault detection performance, robustness and viability of the proposed technique.

  • Robust Detection of Oscillatory Failure Case in Aircraft Control Surface Servo-Loops
    Fault Diagnosis and Fault-Tolerant Control and Guidance for Aerospace Vehicles, 2013
    Co-Authors: Ali Zolghadri, David Henry, Denis Efimov, Jérôme Cieslak, Philippe Goupil

    Abstract:

    This chapter deals with model-based Fault Detection and Diagnosis (FDD) methods which have been recently applied to Oscillatory Failure Case (OFC) in Aircraft Control surface servo-loops. This failure case, related to the Electrical Flight Control System (EFCS), could have an influence on structural loads and Aircraft Controllability. Two methods will be presented and, in order to improve FDD performance and robustness, the tuning of their free design parameters are discussed. The presented methods are nonlinear observer design and fault reconstruction via sliding-mode differentiation. The efficiency of the above techniques will be illustrated through their application to highly representative Aircraft benchmarks, real flight data, and real-time implementation on Airbus test facilities. In addition to thrust Control, the principal means of Controlling an Aircraft is through aerodynamic forces generated by Control surfaces which are generally movable flaps located on the fuselage, wing, and tail. The primary purpose of certain Control surfaces (e.g., elevator, rudder, and ailerons) is to generate Control moments; hence, their resultant forces act at some distance from the Aircraft center of mass. In this section the main Control surfaces and their functions are briefly recalled (see Fig. 3.1).