Systematic Approach to an Improved Electrical Power System Architecture for a Future More Electric Airplane

Breit, J.S.

doi:10.4271/2021-01-0034

Cited by 2 publications

(4 citation statements)

References 20 publications

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Section: Electrohydraulic Actuation Systemsmentioning

confidence: 99%

“…Over the past few years, several EHA designs have been developed for electrical aircraft, for example, J. Breit reported on findings from the Experimental Aircraft Project (EAP) program, which examined and compared the functionality of electrohydraulic servo valves (EHSVs) with direct-drive valves (DDVs) actuators for primary flight control [6]. Figure 3 shows the British Aerospace (BAe) EAP actuator flow diagram, with the control valves driven either by EHSV or DDV.…”

Section: Electrohydraulic Actuation Systemsmentioning

confidence: 99%

“…These components are all integrated into a single unit. The EHA approach has the advantages of both hydraulic and electronic systems, thus providing weight-reduction benefits, increased efficiency, and reliability [6,28] Over the past few years, several EHA designs have been developed for electrical aircraft, for example, J. Breit reported on findings from the Experimental Aircraft Project (EAP) program, which examined and compared the functionality of electrohydraulic servo valves (EHSVs) with direct-drive valves (DDVs) actuators for primary flight control [6]. Figure 3 In the EHSV assembly, two hydraulic systems (HSs), each of which is associated with two EHSVs, drive the actuator.…”

Section: Electrohydraulic Actuation Systemsmentioning

confidence: 99%

“…There are two categories of electric aircrafts, namely: More Electric Aircraft (MEA) and All Electric Aircraft (AEA). These two categories differ from conventional aircrafts as they include electrically driven alternatives to traditional aircraft subsystems [4][5][6]. However, the AEA concept goes as far back as the Second World War, when the US and the UK produced an all-electric military bomber aircraft that had the advantage of simple/clean installation and elimination of oil leakage and oil contamination, hence eradicating the possibility of fire hazards [7][8][9].…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Progress in Redundant Electromechanical Actuators for Aerospace Applications

Annaz,

Kaluarachchi

2023

Aerospace

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The power to move aircraft control surfaces has advanced from being manually generated (by the pilot and transmitted via rods and links) to electrically transmitted (via wires) to operate control surface actuators. Various hydraulic, electromagnetic, and electromechanical architectures have been developed to provide the necessary power and to maintain the expected redundancy. Numerous aircraft actuator system designs have been proposed in the past decades, but a comprehensive review has yet to be undertaken. This review paper aims to fill this gap by providing a critical review of the actuation system designs developed for a variety of aircraft. The review focuses on aircraft actuator system designs, namely: electrohydraulic actuator systems, electromechanical actuator systems, and the force-fighting effect in redundant actuation systems. The significance and operational principle of each actuator system are critically analysed and discussed in the review. The paper also evaluates the solution proposed to address force-fight equalization (or force-fight cancelation) in force or torqued-summed architectures. Future trends in redundant actuation system development with reduced force-fighting effect in aircraft actuator systems are also addressed.

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Section: Electrohydraulic Actuation Systemsmentioning

confidence: 99%

Section: Electrohydraulic Actuation Systemsmentioning

confidence: 99%