Development of a reliable electro-mechanical actuator for primary control surfaces in small aircrafts

Mazzoleni, Mirko; Maccarana, Yamuna; Previdi, Fabio; Pispola, Giulio; Nardi, Marcos Beyer; Perni, F.; Toro, Sergio Fuentes del

doi:10.1109/aim.2017.8014172

Cited by 20 publications

(12 citation statements)

References 17 publications

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“…In data-driven model-based techniques, this knowledge is achieved via experiments, by artificially injecting the major faults and measuring the system response during and after the fault [20,28,29,42,43]. This method provides more accurate predictions, but rigging costs are often prohibitive and the FDI strongly depends on tested conditions.…”

Section: Motivations Of the Researchmentioning

confidence: 99%

“…Many research efforts have been and are made to protect EMAs from jamming, by applying both prognostic and diagnostic monitoring methods, aiming at anticipating (i.e., avoiding), or detecting and isolating the fault, respectively. The prognostic solution, though potentially overwhelming [27][28][29][30], is nowadays far from being applicable to airworthy systems, so that diagnostic approaches are typically preferred [31,32].…”

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: Motivations Of the Researchmentioning

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

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show abstract

“…An example of simplex EMA is given by the actuator developed by UmbraGroup (Italy) through recent R&D activities [44,45,47] (in particular this actuator was used in the first phase of the REPRISE project, see Sect. 4.2.2).…”

Section: Simplex Fail-safe Emamentioning

confidence: 99%

Introduction

Mazzoleni¹,

Rito²,

Previdi³

2021

Advances in Industrial Control

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“…This paper presents a part of the results of the Reliable Electromechanical actuator for PRImary SurfacE with health monitoring (REPRISE) initiative, a EU-H2020 funded project that aims at introducing HM algorithms for primary flight control surfaces EMAs in small aircrafts (aileron, elevator and rudder) [19]. The scope of the REPRISE project is to support the improvement of the Technological Readiness Level (TRL) for a EMA-based flight control system of small aircrafts bringing it to TRL 5.…”

Section: Introductionmentioning

confidence: 99%

Experimental Development of a Health Monitoring Method for Electro-Mechanical Actuators of Flight Control Primary Surfaces in More Electric Aircrafts

et al. 2019

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This paper presents a health monitoring approach for Electro-Mechanical Actuators (EMA). We define four different indicators to continuously evaluate the health state of the system. The four indicators are computed by leveraging the output from a Statistical Process Monitoring (SPM) method based on multivariate statistics, such as the Hotelling's T 2 statistic and the Q statistic. SPM approaches give a dichotomous answer, i.e. the presence/absence of a fault. In this work, we propose four ways to compute a continuous indicator starting from the discrete SPM output, that is better suited for health monitoring. We test the approach using a dataset collected from a large experimental campaign on a 1:1 scale EMA for primary flight controls of small aircrafts, that led to EMA failure. Results show the effectiveness of the method.

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Development of a reliable electro-mechanical actuator for primary control surfaces in small aircrafts

Cited by 20 publications

References 17 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

Introduction

Experimental Development of a Health Monitoring Method for Electro-Mechanical Actuators of Flight Control Primary Surfaces in More Electric Aircrafts

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