Development of a Fault Tolerant Control for Aircraft Electromechanical Actuators

Bennouna, Ouadie; Langlois, Nicolas

doi:10.1109/esars.2012.6387391

Cited by 9 publications

(10 citation statements)

References 13 publications

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“…However, most of the research efforts in the field of FTC were focused on specific limited problems: electro-mechanical actuator failures [39], loss of actuator efficiency [40], partial loss of control [41], aircraft structural damage [34], etc. The need for a holistic approach that is capable of providing a comprehensive and integrated solution in this area has been widely acknowledged [9,42,43].…”

Section: Figure21: General Structure Of Fault-tolerant Control Systemsmentioning

confidence: 99%

Immunity-based accommodation of aircraft subsystem failures

Togayev¹

2017

AEAT

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Immunity-Based Accommodation of Aircraft Subsystem Failures This thesis presents the design, development, and flight-simulation testing of an artificial immune system (AIS) based approach for accommodation of different aircraft subsystem failures. Failure accommodation is considered as part of a complex integrated AIS scheme that contains four major components: failure detection, identification, evaluation, and accommodation. The accommodation part consists of providing compensatory commands to the aircraft under specific abnormal conditions based on previous experience. In this research effort, the possibility of building an AIS allowing the extraction of pilot commands is investigated. The proposed approach is based on structuring the self (nominal conditions) and the non-self (abnormal conditions) within the AIS paradigm, as sets of artificial memory cells (mimicking behavior of T-cells, B-cells, and antibodies) consisting of measurement strings, over pre-defined time windows. Each string is a set of features values at each sample time of the flight including pilot inputs, system states, and other variables. The accommodation algorithm relies on identifying the memory cell that is the most similar to the incoming measurements. Once the best match is found, control commands corresponding to this match will be extracted from the memory and used for control purposes. The proposed methodology is illustrated through simulation of simple maneuvers at nominal flight conditions, different actuators, and sensor failure conditions. Data for development and demonstration have been collected from West Virginia University 6-degreesof-freedom motion-based flight simulator. The aircraft model used for this research represents a supersonic fighter which includes model following adaptive control laws based on non-linear dynamic inversion and artificial neural network augmentation. The simulation results demonstrate the possibility of extracting pilot compensatory commands from the self/non-self structure and the capability of the AIS paradigm to address the problem of accommodating actuator and sensor malfunctions as a part of a comprehensive and integrated framework along with abnormal condition detection, identification, and evaluation. DEDICATION To my mother Gulnara Yezhebayeva and my grandparents,

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Section: Figure21: General Structure Of Fault-tolerant Control Systemsmentioning

confidence: 99%

Immunity-based accommodation of aircraft subsystem failures

Togayev¹

2017

AEAT

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“…Given the sparse implementation of EMAs in today's commercial aircraft actuation systems, Electro-hydraulic Actuators (EHA) are considered the intermediate solution between hydromechanical and electromechanical actuation systems (Bennett, 2010). EHAs are essentially a hybrid electrical and hydraulic device where the actuator is hydraulically operated with the hydraulic fluid self-contained and pressurised by an inbuilt motor to drive the actuation mechanism (Churn et al 1998).…”

Section: Ballscrew Assemblymentioning

confidence: 99%

“…EHAs are viewed as advantageous over conventional hydraulic systems with increased fluid pressure and power density during actuations (Moir et al 2008). Loss of operation would inhibit the hydraulic rod in exerting a force thus defaulting to damping action allowing for an adequate fail-safe mechanism by enabling other actuators to fulfil the actuation (Bennett, 2010). This makes EHAs the preferred choice in safety critical applications today.…”

Section: Ballscrew Assemblymentioning

confidence: 99%

Evaluating Strategies to Mitigate Jamming in Electromechanical Actuators for Safety Critical Applications

Hussain,

Burrow,

Henson

et al. 2017

PHMAP_CONF

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In this paper various techniques to mitigate jamming in Electromechanical Actuators (EMA) for safety critical applications in aerospace are evaluated. This paper highlights and assesses what has already been achieved and thechallenges still to be addressed. Through Hierarchical Process Modelling (HPM), it was identified that Prognostics and Health Monitoring (PHM) and achieving fault tolerant designs in EMAs could be considered as means to mitigate jamming. The evaluation of past research revealed that achieving a fault tolerant EMA system through a reliable and robust anti-jamming system is currently at an early development stage for implementation within safety critical systems due to the increased design complexity (the antijamming system may even require PHM functionality itself). It was concluded that a hybrid diagnostic approach to predict the onset of jamming would be the most optimal approach by using a combination of model based and data-driven techniques to capture any discrepancies between the predicted and observed behaviour to isolate and identify faults. Furthermore, in order to achieve a robust and reliable hybrid diagnostics functionality (to mitigate EMA ballscrew jamming), recommendations were made to improve modelling fidelity and test stand analysis methodology, these are discussed in more detail in this paper.

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“…An alternative approach, which this article refers to, is to use high-fidelity actuator models that are experimentally validated with reference to the normal condition only, but also capable of simulating the faulty behaviour by physical first principles. 13,14 The basic idea underlying this work is that major faults in position-controlled flight controls can be detected by a position-tracking monitor (PTM), provided that an accurate predictor is used. 15,16 This would simplify the software complexity as well as the number of additional sensors needed for the health monitoring functions.…”

Section: Introductionmentioning

confidence: 99%

Health monitoring of electromechanical flight actuators via position-tracking predictive models

Rito

Schettini

2018

Advances in Mechanical Engineering

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This article deals with the development and performance characterisation of model-based health monitoring algorithms for the detection of faults in an electromechanical actuator for unmanned aerial system flight controls. Two real-time executable position-tracking algorithms, based on predictors with different levels of complexity, are developed and compared in terms of false alarm rejection and fault detection capabilities, using a high-fidelity model of the actuator in which different types of faults are injected. The algorithms' performances are evaluated by simulating flight manoeuvres with the actuator in normal operation as well as with relevant faults (motor coil faults, motor magnet degradation, voltage supply decrease). The results demonstrate that an accurate position-tracking monitor allows to obtain a prompt fault detection and fail-safe mode engagement, while more detailed monitoring functions can be used for fault isolation only.

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Development of a Fault Tolerant Control for Aircraft Electromechanical Actuators

Cited by 9 publications

References 13 publications

Immunity-based accommodation of aircraft subsystem failures

Immunity-based accommodation of aircraft subsystem failures

Evaluating Strategies to Mitigate Jamming in Electromechanical Actuators for Safety Critical Applications

Health monitoring of electromechanical flight actuators via position-tracking predictive models

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