scholarly journals Design Considerations of Fault-Tolerant Electromechanical Actuator Systems for More Electric Aircraft (MEA)

2018 ◽  
Author(s):  
Shaohong Zhu ◽  
Tom Cox ◽  
Zeyuan Xu ◽  
Chris Gerada ◽  
Chen Li
Keyword(s):  
Fault Tolerant ◽  
Electromechanical Actuator ◽  
Design Considerations ◽  
Electric Aircraft ◽  
More Electric Aircraft

scholarly journals Active Fault-Tolerant Control Strategy for More Electric Aircraft under Actuation System Failure

Actuators ◽  
2020 ◽  
Vol 9 (4) ◽  
pp. 122
Author(s):  
Xiaozhe Sun ◽  
Xingjian Wang ◽  
Zhiyuan Zhou ◽  
Zhihan Zhou
Keyword(s):  
Hydraulic System ◽  
Active Fault ◽  
Fault Tolerant ◽  
Hydraulic Loss ◽  
System Failure ◽  
Actuation System ◽  
Electric Aircraft ◽  
Differential Thrust ◽  
More Electric Aircraft ◽  
Tail Damage

The aircraft hydraulic system is very important for the actuation system and its failure has led to a number of catastrophic accidents in the past few years. The reasons for hydraulic loss can be leakage, blockage, and structural damage. Fortunately, the development of more electric aircraft (MEA) provides a new means of solving this difficult problem. This paper designs an active fault tolerant control (AFTC) method for MEA suffering from total hydraulic loss and actuation system failure. Two different kinds of scenarios are considered: leakage/blockage and vertical tail damage. With the application of the dissimilar redundant actuation system (DRAS) in MEA, a switching mechanism can be used to change the hydraulic actuation (HA) system into an electro-hydrostatic actuation (EHA) system when the whole hydraulic system fails. Taking account of the gap between HA and EHA, a degraded model is built. As for vertical tail damage, engine differential thrust control is adopted to help regain lateral-directional stability. The engine thrust dynamics are modeled and the mapping relationship between engine differential thrust and rudder deflection is formulated. Moreover, model reference control (MRC) and linear quadratic regulator (LQR) are used to design the AFTC method. Comparative simulation with the NASA generic transportation model (GTM) is carried out to prove the proposed strategy.

scholarly journals Thermal analysis of fault-tolerant electrical machines for more electric aircraft applications

2018 ◽  
Vol 2018 (13) ◽  
pp. 461-467 ◽  
Author(s):  
Vincenzo Madonna ◽  
Paolo Giangrande ◽  
Chris Gerada ◽  
Michael Galea
Keyword(s):  
Thermal Analysis ◽  
Fault Tolerant ◽  
Electrical Machines ◽  
Electric Aircraft ◽  
More Electric Aircraft

Design of a 250kW, Fault-Tolerant PM Generator for the More-Electric Aircraft

2005 ◽  
Author(s):  
Jason Ede ◽  
Geraint Jewell ◽  
Kais Atallah ◽  
David Powell ◽  
John Cullen ◽  
...  
Keyword(s):  
Fault Tolerant ◽  
Electric Aircraft ◽  
More Electric Aircraft

A fuzzy logic based method for fault tolerant hierarchical load management of more electric aircraft

2018 ◽  
Vol 233 (10) ◽  
pp. 3846-3856 ◽  
Author(s):  
Yuxue Ge ◽  
Bifeng Song ◽  
Yang Pei ◽  
Yves Mollet ◽  
Johan Gyselinck
Keyword(s):  
Fuzzy Logic ◽  
Fault Tolerant ◽  
Load Management ◽  
Auxiliary Power Unit ◽  
Auxiliary Power ◽  
Electric Aircraft ◽  
Management Method ◽  
Adaptive Power ◽  
Electrical Loads ◽  
More Electric Aircraft

With the increasing number of electrical loads, load management of the more electric aircraft becomes crucial for reliability and efficiency. One of the major challenge is to develop an optimal and reliable adaptive power control. This paper presents a three-level load management method with dedicated time steps for fault tolerance and increasing calculation efficiency. Both the operative mode and the health level of the loads are taken into account in the control using fuzzy logic. The electrical system of a V-tail more electric aircraft that consists of a generator, an auxiliary power unit, and several AC/DC buses and loads is examined by the proposed method in normal and faulty cases. Compared with some conventional methods, the proposed load management method has the advantage of efficiently shedding loads according to the power imbalance and the fault situation.

scholarly journals Intelligent Fault-Tolerant Control for AC/DC Hybrid Power System of More Electric Aircraft

Aerospace ◽  
2021 ◽  
Vol 9 (1) ◽  
pp. 4
Author(s):  
Lingfei Xiao ◽  
Robert R. Sattarov ◽  
Peisong Liu ◽  
Cong Lin
Keyword(s):  
Power System ◽  
Control Method ◽  
Fault Tolerant ◽  
Electrical Power ◽  
Active Power Filter ◽  
Aircraft Engine ◽  
Electrical Power System ◽  
Power Filter ◽  
Electric Aircraft ◽  
More Electric Aircraft

This paper presents a novel intelligent fault-tolerant control method for a kind of more electric aircraft AC/DC hybrid electrical power system, in order to ensure the safe operation of the engine and improve the power supply quality. The more electric aircraft electrical power system was combined with an aircraft engine, two generators, two AC/DC rectifiers, two DC/AC inverters, DC loads, and AC loads. A multi-objective optimization intelligent sliding mode fault-tolerant controller was obtained for aircraft engine with actuator faults. Each of AC/DC rectifiers is 12-pulse autotransformer rectifier unit with active power filter. Active power filter was used to realize the desired performance of DC bus. Intelligent fractional order PI controller is presented for AC/DC rectifier by considering multiple performance indexes. In order to guarantee the AC-side has satisfying voltage, current, and frequency, no matter the sudden change of AC load that happens or DC/AC fault that occurs, the virtual synchronous generator control method was used for DC/AC inverters. Simulation results verify the effective of the proposed more electric aircraft AC/DC hybrid electrical power system.

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