The Experts below are selected from a list of 74493 Experts worldwide ranked by ideXlab platform

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, Ali Zolghadri, Denis Efimov, 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.

  • 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, Jérôme Cieslak, David Henry, Denis Efimov, 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).

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.

  • A Method for Actuator Lock-in-place Failure Detection in Aircraft Control Surface Servo-loops
    2014
    Co-Authors: Jérôme Cieslak, Ali Zolghadri, Denis Efimov, 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.

  • 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, Jérôme Cieslak, David Henry, Denis Efimov, 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).

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, Jérôme Cieslak, David Henry, Denis Efimov, 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).

  • Early detection of Aircraft Control surface faults by dedicated Kalman filtering: runaways and jammings
    2011
    Co-Authors: Anca Gheorghe, Jérôme Cieslak, David Henry, Ali Zolghadri, Philippe Goupil, Rémy Dayre, Hervé Leberre
    Abstract:

    Early and robust detection of runaway (hard over) and jamming (locked in place) of Aircraft Control surfaces is an important issue in the process of overall Aircraft structural design optimization. Today, system design objectives originating from structural load constraints are more and more stringent for satisfying the newer societal imperatives towards future "sustainable" Aircraft (quieter, cleaner, smarter and more affordable). In this paper, a simple model-based solution is proposed to address this problem. The proposed strategy provides good performance and robustness and requires technical low computational effort for implementation. The proposed approach does not substitute for already in place physical redundancy-based monitoring system, but it can be seen as a useful supplement that properly exploits the physical redundancy. So, from a practical point of view, a big advantage of the proposed scheme is that it can be embedded within the structure of in-service monitoring system as a part of the Flight Control Computer (FCC) software. The methodology is based on a dedicated Kalman filtering. Simulation results using in-flight recorded data sets provided by Airbus and a highly representative Aircraft benchmark are presented to demonstrate the efficiency of the developed technique.

Jérôme Cieslak - 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, Ali Zolghadri, Denis Efimov, 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.

  • 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, Jérôme Cieslak, David Henry, Denis Efimov, 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).

  • Early detection of Aircraft Control surface faults by dedicated Kalman filtering: runaways and jammings
    2011
    Co-Authors: Anca Gheorghe, Jérôme Cieslak, David Henry, Ali Zolghadri, Philippe Goupil, Rémy Dayre, Hervé Leberre
    Abstract:

    Early and robust detection of runaway (hard over) and jamming (locked in place) of Aircraft Control surfaces is an important issue in the process of overall Aircraft structural design optimization. Today, system design objectives originating from structural load constraints are more and more stringent for satisfying the newer societal imperatives towards future "sustainable" Aircraft (quieter, cleaner, smarter and more affordable). In this paper, a simple model-based solution is proposed to address this problem. The proposed strategy provides good performance and robustness and requires technical low computational effort for implementation. The proposed approach does not substitute for already in place physical redundancy-based monitoring system, but it can be seen as a useful supplement that properly exploits the physical redundancy. So, from a practical point of view, a big advantage of the proposed scheme is that it can be embedded within the structure of in-service monitoring system as a part of the Flight Control Computer (FCC) software. The methodology is based on a dedicated Kalman filtering. Simulation results using in-flight recorded data sets provided by Airbus and a highly representative Aircraft benchmark are presented to demonstrate the efficiency of the developed technique.

Florian Holzapfel - One of the best experts on this subject based on the ideXlab platform.

  • A robust Aircraft Control approach in the presence of wind using viability theory
    2017 Australian and New Zealand Control Conference (ANZCC), 2017
    Co-Authors: Johannes Diepolder, Varvara Turova, Patrick Piprek, Nikolai Botkin, Florian Holzapfel
    Abstract:

    This paper presents a Control concept for the application of viability kernels for Aircraft Control in the presence of wind disturbances. The viability (leadership) kernel of an appropriate conflict Control problem with state constraints is computed using a grid approximation. In this differential game formulation, the first player is represented by the Aircraft Controls and the second player by the wind disturbances. The viability kernel represents a subset in the state space, in which the Aircraft can be held arbitrarily long even if the opposing player uses any admissible Control. Due to the curse of dimensionality in the grid solution, the computation of the viability kernel is restricted to low dimensional state spaces, which poses a challenge for the application in Aircraft Control. In our approach, the viability kernel is computed in the state space of the translational dynamics and the attitude kinematics. This reduces the dimensionality of the viability kernel to a six dimensional state space that can be handled by grid computers. The trajectory from the viability kernel solution is then tracked by the inner-loop Controller based on a nonlinear dynamic inversion (NDI) Control structure. The approach is illustrated using a simplified A300 Aircraft model for cruise flight in the presence of wind.

  • Viability Approach to Aircraft Control in Wind Shear Conditions
    Advances in Dynamic and Mean Field Games, 2017
    Co-Authors: Nikolai D. Botkin, Varvara Turova, Johannes Diepolder, Matthias Bittner, Florian Holzapfel
    Abstract:

    This paper addresses the analysis of Aircraft Control capabilities in the presence of wind shears. The cruise flight phase (flying at the established level with practically constant configuration and speed) is considered. The study utilizes a point-mass Aircraft model describing both vertical and lateral motions. As a particular case, a reduced model of lateral motion is derived from the full one. State variables of the models are constrained according to Aircraft safety conditions, and differential games where a guiding system, the first player, works against wind disturbances, the second player, are considered. Viability theory is used to find the leadership kernel, the maximal subset of the state constraint where the Aircraft trajectories can remain arbitrary long if the first player utilizes an appropriate feedback Control, and the second player generates any admissible disturbances. The computations are based on a theoretical background resulting in a grid method developed by the authors. The corresponding software is implemented on a multiprocessor computer system.