Model-based design and experimental verification of a monitoring concept for an active-active electromechanical aileron actuation system

Arriola, David; Thielecke, Frank

doi:10.1016/j.ymssp.2017.02.039

Cited by 27 publications

(14 citation statements)

References 8 publications

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“…The reference actuator is a fault-tolerant EMA (Figure 1a), basically composed of In deterministic model-based techniques, which this paper refers to, the knowledge of dynamics with faults is derived from a mathematical model, capable of simulating the faults occurrence by physical first-principles [33][34][35][36], which is experimentally-validated with reference to normal and/or regime faulty conditions. Oppositely to the data-driven case, this method generally provides less accurate predictions, but it is cost-effective, it allows to verify FDI functionalities in extreme conditions and (above all) permits to generalise the FDI algorithms validity to similar equipments (i.e., governed by similar equations).…”

Section: System Architecturementioning

confidence: 99%

“…The diagnostic monitoring requires that fault detection and isolation (FDI) algorithms are implemented and real-time executed by onboard control electronics [33][34][35][36], so that, in case of a detected jamming, redundant mechanical channels or unlock devices can be engaged [37,38]. Depending on how the mechanical redundancy is applied, after the fault compensation, the EMA can maintain its functionality, or it can be reverted in a stand-by mode, so that jamming-operative or jamming-safe EMAs are respectively obtained.…”

Section: Introduction 1research Contextmentioning

confidence: 99%

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Model-Based Condition-Monitoring and Jamming-Tolerant Control of an Electro-Mechanical Flight Actuator with Differential Ball Screws

Rito

Luciano²,

Borgarelli

et al. 2021

Actuators

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The work deals with the development of deterministic model-based condition-monitoring algorithms for an electromechanical flight control actuator with fault-tolerant architecture, in which two permanent magnets synchronous motors are coupled with differential ball screws in speed-summing paradigm, so that the system can operate even after a motor fault, an inverter fault or a mechanical jamming. To demonstrate the potential applicability of the system for safety-critical aerospace applications, the failure transients related to major fault modes have to be characterised and analysed. By focusing the attention to jamming faults, a detailed nonlinear model of the actuator is developed from physical first principles and experimentally validated in both time and frequency domains for normal condition and with different types of jamming. The validated model is then used to design the condition-monitoring algorithms and to characterize the system failure transient, by simulating mechanical blocks in different locations of the transmission. The operability after the fault, obtained via fault-tolerant control strategy and position regulator reconfiguration, is also verified, by highlighting and discussing possible enhancements and criticalities.

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Section: System Architecturementioning

confidence: 99%

Section: Introduction 1research Contextmentioning

confidence: 99%

Model-Based Condition-Monitoring and Jamming-Tolerant Control of an Electro-Mechanical Flight Actuator with Differential Ball Screws

Rito

Luciano²,

Borgarelli

et al. 2021

Actuators

View full text Add to dashboard Cite

show abstract

“…Said layout involves flight control redundancies and their failure criticality for a safe landing. Examples of recent research approaches for developing fault-tolerant EMAs can be found in [3][4][5][6][7][8].…”

Section: Introductionmentioning

confidence: 99%

Design and Evaluation of Fault-Tolerant Electro-Mechanical Actuators for Flight Controls of Unmanned Aerial Vehicles

Ismail

Wiedemann²,

Bosch

et al. 2021

Actuators

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Electro-mechanical actuators (EMAs) are a primary actuation technology for unmanned aerial vehicles (UAVs). Intensive research has been conducted for designing and evaluating fault-tolerant EMAs for flight controls of UAVs to ensure their compliance with new airworthiness requirements for safe operation over civilian zones. The state-of-the-art research involves several fault-tolerant architectures for EMAs based on parallel electric motors or a single motor with internal fault-tolerant features. In this study, a fault-tolerant architecture is introduced, comprised of two serial electric motors driven by two isolated controllers and a health monitoring system. The procedures of developing various fault-tolerant features are discussed with a deep focus on designing health monitoring functions and evaluating their influence on the overall actuator stability and availability. This work has been conducted and evaluated based on operational data for ALAADy: a heavy gyrocopter-type UAV at DLR (German Aerospace Center).

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“…In the past decade, redundant technology has become a key technology for the aerospace sector because of its high reliability. Among the solutions identified for the redundancy electromechanical servo system, the dual-motor differential electromechanical servo system has a promising future and important significance [1][2]. Compared with single-channel servos, the dual-channel design consists of two motors which in the active-active working mode can effectively use resources, meanwhile, the redundant design greatly improves the reliability of the system.…”

Section: Introductionmentioning

confidence: 99%

The switching control strategy of redundant electromechanical servo system based on the compound sliding mode control

Li¹,

Yu²,

Jiang³

2021

E3S Web Conf.

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Aiming to resolve the limitations of robustness and stability in switching working modes of dual redundancy electric servo system, a control strategy based on sliding mode control is suggested. By analyzing the electromechanical servo system’s basic structure and working theory, a mathematical model is created to enable the design of new control functions. Taking into account the influence of the internal parameter perturbation of the electromechanical servo system during the switching between working modes, the sliding mode control is used to enhance system robustness, and the method of combining the latest saturation function and the exponential reaching law is used to minimize the system chattering. The simulation results and analysis show that the control strategy can effectively improve the robustness and control accuracy of the system.

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Model-based design and experimental verification of a monitoring concept for an active-active electromechanical aileron actuation system

Cited by 27 publications

References 8 publications

Model-Based Condition-Monitoring and Jamming-Tolerant Control of an Electro-Mechanical Flight Actuator with Differential Ball Screws

Model-Based Condition-Monitoring and Jamming-Tolerant Control of an Electro-Mechanical Flight Actuator with Differential Ball Screws

Design and Evaluation of Fault-Tolerant Electro-Mechanical Actuators for Flight Controls of Unmanned Aerial Vehicles

The switching control strategy of redundant electromechanical servo system based on the compound sliding mode control

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