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

Rito, Gianpietro Di; Luciano, Benedetto; Borgarelli, Nicola; Nardeschi, Marco

doi:10.3390/act10090230

Cited by 8 publications

(4 citation statements)

References 43 publications

(70 reference statements)

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“…Di Rito et al. [130] developed a fault‐tolerant EMA system that was able to detect and isolate jamming fault in the ball screw pair and accordingly change its operative modes with a latency lower than 90 ms. To sum up, passive fault‐tolerant control strategies can only be activated when the EMA is close to failure and the control performance is seriously affected. They do not reflect the full functions of the DPHM system.…”

Section: Ema Dphm Methodsmentioning

confidence: 99%

“…In addition, Patel et al [129] replace the position signal collected by sensors with the signal estimated by the observer model for feedback control when the failure of the position feedback sensor is detected. Di Rito et al [130] developed a fault-tolerant EMA system that was able to detect and isolate jamming fault in the ball screw pair and accordingly change its operative modes with a latency lower than 90 ms. To sum up, passive fault-tolerant control strategies can only be activated when the EMA is close to failure and the control…”

Section: Fault-tolerant Controlmentioning

confidence: 99%

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A review of fault diagnosis, prognosis and health management for aircraft electromechanical actuators

Yin

Chen

et al. 2022

IET Electric Power Appl

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As More/All Electric Aircraft gradually become a research hotspot, electromechanical actuators (EMAs), which can directly convert electrical energy into mechanical energy, have gained more and more attention. However, since the reliability of EMA cannot meet the requirements of actual aircrafts, the practical application of EMA is severely limited. Therefore, fault diagnosis, prognosis and health management (DPHM), which can realise condition‐based maintenance (CBM), has become the key technology in the application of EMA. The aim is to summarise the research on EMA fault modes, fault diagnosis, prognosis and health management systematically and comprehensively. First, the basic structure and common fault modes of EMAs are introduced, and the failure mechanism of EMA is studied. Then, the algorithms of DPHM for EMAs are reviewed in detail. The perception strategies of data acquisition are analysed, and the EMA fault diagnosis methods, including model‐based and data‐driven methods, are reviewed. The research of remaining useful life (RUL) prediction and fault‐tolerant control are introduced. After that, some problems of the existing research on EMA DPHM and their potential solutions are put forward. Finally, several possible developing directions of research on EMA DPHM are predicted.

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Section: Ema Dphm Methodsmentioning

confidence: 99%

Section: Fault-tolerant Controlmentioning

confidence: 99%

A review of fault diagnosis, prognosis and health management for aircraft electromechanical actuators

Yin

Chen

et al. 2022

IET Electric Power Appl

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“…The LVDT provides excellent behavior in terms of high resolution, robustness, and durability [ 1 , 2 , 3 ]. Many applications of the LVDT are found in the fields of industrial process control [ 3 , 4 , 5 , 6 ], building construction [ 7 ], automobiles [ 8 , 9 ], military equipment [ 10 , 11 , 12 ], scientific and medical equipment [ 12 , 13 ], and robotics [ 14 , 15 ]. All applications of the LVDT are used to measure position, force, flow, displacement, and pressure.…”

Section: Introductionmentioning

confidence: 99%

Linear-Range Extension for Linear Variable Differential Transformer Using Hyperbolic Sine Function

Rerkratn

Tongcharoen

Petchmaneelumka

et al. 2022

Sensors

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In this paper, a circuit technique to extend the measuring range of a linear variable differential transformer (LVDT) is proposed. The transfer characteristic of the LVDT contains the odd function form of the cubic polynomial. Therefore, the measuring range of a commercial LVDT is linear in a narrow range compared to its physical dimensions. The wide measuring range of the LVDT requires a large structure of the LVDT, which increases the scale and the cost of the measurement system. The measuring range of the LVDT can be linearly extended to the maximum of the stroke range using the proposed technique. The realization of the proposed technique is based on the use of the hyperbolic sine (sinh) function of the electronic circuit building block, named the class AB bipolar amplifier. The class AB bipolar amplifier can be obtained by the current feedback operational amplifier (CFOA). The circuit of the proposed technique requires two CFOAs and an operational transconductance amplifier (OTA) as the active devices and all devices used in the proposed technique to synthesize the sinh function are commercially available. The proposed technique exhibits an ability to compensate for the nonlinear characteristic of the LVDT without digital components. The proposed technique is attractive in terms of its simple circuit configuration, small size, and low cost. The linear range extension of the LVDT used in this paper is significantly increased with a maximum error of about 18.3 μm of 6.2 mm at the full stroke range or the full-scale percentage error of about 0.295%. The results indicate that the proposed technique provides excellent performance to extend the measuring range of the LVDT without modifying the LVDT structure.

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“…Model-based PHM uses a representation of the system (or component) of interest, using a set of differential Equations [8][9][10]. If properly modeled, the system status can be assessed with good accuracy and fault propagation is generally embedded in the fault model [11,12].…”

Section: Introductionmentioning

confidence: 99%

An Improved Fault Identification Method for Electromechanical Actuators

et al. 2022

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Adoption of electromechanical actuation systems in aerospace is increasing, and so reliable diagnostic and prognostics schemes are required to ensure safe operations, especially in key, safety-critical systems such as primary flight controls. Furthermore, the use of prognostics methods can increase the system availability during the life cycle and thus reduce costs if implemented in a predictive maintenance framework. In this work, an improvement of an already presented algorithm will be introduced, whose scope is to predict the actual degradation state of a motor in an electromechanical actuator, also providing a temperature estimation. This objective is achieved by using a properly processed back-electromotive force signal and a simple feed-forward neural network. Good prediction of the motor health status is achieved with a small degree of inaccuracy.

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

Cited by 8 publications

References 43 publications

A review of fault diagnosis, prognosis and health management for aircraft electromechanical actuators

A review of fault diagnosis, prognosis and health management for aircraft electromechanical actuators

Linear-Range Extension for Linear Variable Differential Transformer Using Hyperbolic Sine Function

An Improved Fault Identification Method for Electromechanical Actuators

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