Safety Analysis of Actuation System of More Electric Aircraft

2018 ◽  
Author(s):  
Bo Yu ◽  
Shuai Wu ◽  
Zongxia Jiao ◽  
Yaoxing Shang ◽  
Yan Zhou
Keyword(s):  
Safety Analysis ◽  
Actuation System ◽  
Electric Aircraft ◽  
More Electric Aircraft

scholarly journals Architecture Optimization of More Electric Aircraft Actuation System

2011 ◽  
Vol 24 (4) ◽  
pp. 506-513 ◽  
Author(s):  
Haitao QI ◽  
Yongling FU ◽  
Xiaoye QI ◽  
Yan LANG
Keyword(s):  
Actuation System ◽  
Electric Aircraft ◽  
Architecture Optimization ◽  
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 Incremental Modeling and Simulation of Mechanical Power Transmission for More Electric Aircraft Flight Control Electromechanical Actuation System Application

2016 ◽  
Author(s):  
Jian Fu ◽  
Jean-Charles Maré ◽  
Yongling Fu
Keyword(s):  
Flight Control ◽  
Power Transmission ◽  
Free Play ◽  
Fault Analysis ◽  
Mechanical Power ◽  
Actuation System ◽  
Aircraft Fuel ◽  
Electric Aircraft ◽  
Aircraft Flight Control ◽  
More Electric Aircraft

In the field of more electric aircraft, electromechanical actuators (EMAs) are becoming more and more attractive because of their outstanding benefits of aircraft fuel reduction, maintenance costs saving, and system flexibility improvement. For aerospace electromechanical actuator applications, mechanical power transmission is critical for safety, in which reflected inertia to load, heat generated by energy losses and faults due to jamming, free-play and free-run are specific issues. According to the system-engineering process and simulation-aided design, this communication proposes an incremental approach for the virtual prototyping of EMA mechanical power transmission. Resorting to the Bond-graph formalism, the parasitic effects are progressively introduced and realism of models is increased step-by-step. Finally, the numerical implementations are presented and compared with basic, advanced and full models of mechanical power transmission in AMESim environment. Multi-level submodels are available and can be re-used for preliminary sizing, thermal balance verification and response to fault analysis.

Research on Performances of Hybrid Actuation System with Dissimilar Redundancies

2012 ◽  
Vol 430-432 ◽  
pp. 1559-1563 ◽  
Author(s):  
Li Ming Yu ◽  
Zi Qing Ye
Keyword(s):  
Operating Mode ◽  
Development Trend ◽  
Hydraulic Actuator ◽  
Actuation System ◽  
Electric Aircraft ◽  
Hybrid Actuation ◽  
Actuation Systems ◽  
The Development Trend ◽  
More Electric Aircraft ◽  
Mode A

Hybrid actuation system (HAS) with dissimilar redundancies conforms to the development trend of future actuation systems in more electric aircraft (MEA). Hybrid Actuation system is composed of a traditional servo valve controlled hydraulic actuator (SHA) and an electro-hydraulic actuator (EHA). It has two operating models, active/passive mode (A/P) and active/active mode (A/A). In A/A model both actuators are actively controlled. Corresponding to A/A model, SHA is actively controlled and EHA is passively controlled in A/P model. The hybrid actuation system is built in the AMESim simulation environment, comparative analysis is performed when system operates in these two modes, such as signal response and force fighting. The simulation results provide a guideline to determine the specific operating mode of the system in different circumstances.

Efficiency analysis of moving-magnet linear oscillating motor with dual-resonance for linear electro-hydrostatic actuator

2016 ◽  
Vol 231 (13) ◽  
pp. 2487-2501 ◽  
Author(s):  
Tianyi Wang ◽  
Zongxia Jiao ◽  
Liang Yan
Keyword(s):  
Power Factor ◽  
High Power ◽  
High Efficiency ◽  
High Reliability ◽  
Actuation System ◽  
High Power Factor ◽  
Electric Aircraft ◽  
Dual Resonance ◽  
More Electric Aircraft ◽  
Moving Magnet

More-electric aircraft draws considerable attention due to its high efficiency, high reliability, and easy maintenance. Linear electro-hydrostatic actuator is a novel linear actuation system suitable for more-electric aircraft, and offers many advantages over traditional rotary electro-hydrostatic actuator. However, it requires high-frequency reciprocate actuation of linear oscillating motors with both high efficiency and high power factor. In this study, a novel moving-magnet tubular linear oscillating motor with dual-resonance is proposed for linear electro-hydrostatic actuator applications to achieve high efficiency and high power factor simultaneously. Firstly, system impedance model is set up analytically, which helps to analyze the influence of structure parameters on system performance. Based on this model, working efficiency and power factor are compared with the nonresonance design, and validated by experimental results. In order to take real scenario into considerations, the nonlinearity of motor and rectangular-type load is also analytically derived and analyzed with effective resonant frequency tracking method proposed. It shows that dual-resonance design does increase system efficiency and power factor, and can be applied in linear electro-hydrostatic actuator system for more-electric aircraft effectively.

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