Review on electro hydrostatic actuator for flight control

Alle, Navatha; Hiremath, Somashekhar S.; Singaperumal, M.; Subramaniam, Karunanidhi; Talukdar, Apratim

doi:10.1080/14399776.2016.1169743

Cited by 94 publications

(57 citation statements)

References 32 publications

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“…For example, the PMSM can be an appropriate type when an alternating current power supply directly drives a servo motor. 47 The motor controller is used to control the speed and direction by windings' electrical switch through power electronic devices. An empirical mass estimation of a BLDC motor and its power electronics based on torque-speed characteristics can be referred to Torabzadeh-Tari.…”

Section: Architecture Of Emamentioning

confidence: 99%

A review of electromechanical actuators for More/All Electric aircraft systems

Qiao

Liu

Shi

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part C:

170

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Conventional hydraulic actuators in aircraft systems are high maintenance and more vulnerable to high temperatures and pressures. This usually leads to high operating costs and low efficiency. With the rapid development of More/All Electric technology, power-by-wire actuators are being broadly employed to improve the maintainability, reliability, and manoeuvrability of future aircraft. This paper reviews the published application and development of the airborne linear electromechanical actuator. First, the general configuration, merits, and limitations of the gear-drive electromechanical actuator and the direct-drive electromechanical actuator are analysed. Second, the development state of the electromechanical actuator testing systems is elaborated in three aspects, namely the performance testing based on room temperature, testing in a thermal vacuum environment, and iron bird. Common problems and tendencies of the testing systems are summarized. Key technologies and research challenges are revealed in terms of fault-tolerant motor, high-thrust mechanical transmission, multidisciplinary modelling, thermal management, and thermal analysis. Finally, the trend for future electromechanical actuators in More/All Electric Aircraft applications is summarized, and future research on the airborne linear electromechanical actuators is discussed.

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Section: Architecture Of Emamentioning

confidence: 99%

A review of electromechanical actuators for More/All Electric aircraft systems

Qiao

Liu

Shi

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part C:

170

View full text Add to dashboard Cite

show abstract

“…The system's power matching is achieved by designing reasonable control laws to solve the contradiction between dynamic performance and efficiency. However, the conventional one requires an independent hydraulic system or an electric drive system to control the pump displacement, as well the external additional hydraulic energy, motor and other accessories increase the volume and quality of the system [21][22][23][24][25][26].…”

Section: Introductionmentioning

confidence: 99%

Research on Power Matching and Energy Optimal Control of Active Load-Sensitive Electro-Hydrostatic Actuator

et al. 2021

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Electro-hydrostatic actuator (EHA) is an important type of power-by-wire (PBW) which is a highly integrated closed volume control system with the advantages of high reliability, high efficiency and easy maintenance. However, under heavy load conditions, a large amount of heat the EHA motor produces affects the system's working time and even the system life, which restricts the widespread application of EHA systems. In order to solve the problem of motor heating and the contradiction between high dynamics and high efficiency of the EHA system, a novel active load-sensitive principle and structure of EHA system is proposed based on the load-sensitive principle. The active load-sensitive EHA (ALS-EHA) is a dual control variable system consisting of a motor pump main loop and a load-sensitive loop. As for the latter, the system load pressure is introduced into a special designed and optimized pressure fellow valve (PFV). The valve outlet is connected to the plunger pump swash plate variable mechanism. The EHA pump displacement is actively adjusted by controlling the current input to PFV. The two-degree-of-freedom cooperative control for the output flow of the pump can be implemented by adjusting the motor speed and the pump displacement. An energy optimal robust control law based on fuzzy and disturbance compensation is presented for the control architecture. The simulation results show that the ALS-EHA system based on the control law proposed in this paper can effectively reduce the motor heat while ensuring the dynamic performance of the system.

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“…As an important part of the advanced flight actuation system, electro-hydrostatic actuators (EHAs) have been widely researched, developed, and successfully used on several models of commercial and military aircrafts [1][2][3]. EHAs implement the idea of distributed actuation.…”

Section: Introductionmentioning

confidence: 99%

Design, Analysis, and Verification of an Electro- Hydrostatic Actuator for Distributed Actuation System

Zhang

Zimeng

2020

Sensors

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In order to provide a simplified and low-cost solution of the terminal for a distributed actuation system, this paper proposes an electro-hydrostatic actuator (EHA) based on the linear drive principle. The proposed actuator is directly driven by a linear pump with a collaborative rectification mechanism, whose performance relies on the collaboration of the internal two units. A pair of linear oscillating motors are employed to drive the two pump units respectively. The control of the actuator is based on the modulation of the oscillating amplitude, frequency, and phase difference of the two motors. The advantage of this actuator is that no more valve control is needed to rectify the linear pump besides the high efficiency of the direct pump drive. In this paper, both schematic and detailed structure of the actuator is presented. The kinematic and dynamic characteristics are analyzed and modeled, based on which the control method is proposed. The experiments verify the validity of the actuator structure and control.

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Review on electro hydrostatic actuator for flight control

Cited by 94 publications

References 32 publications

A review of electromechanical actuators for More/All Electric aircraft systems

A review of electromechanical actuators for More/All Electric aircraft systems

Research on Power Matching and Energy Optimal Control of Active Load-Sensitive Electro-Hydrostatic Actuator

Design, Analysis, and Verification of an Electro- Hydrostatic Actuator for Distributed Actuation System

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