Performance analysis of electrical flight control actuation system in a commercial transport aircraft

dc.contributor.authorErcan, Hamdi
dc.contributor.authorAkin, Mustafa
dc.date.accessioned2026-08-12T17:20:15Z
dc.date.issued2022
dc.departmentFırat Üniversitesi
dc.description.abstractPurpose In more than 100 years of aviation, significant progress has been made in flight control systems. The aircrafts that have entered service for the past ten years tend towards power-by-wire flight control with electrical actuators. The purpose of this study is to analyse the effects of electrical actuation on power consumption, weight and fuel consumption on a commercial transport aircraft. Design/methodology/approach The Airbus A321-200 aircraft was chosen as a case study for analysing the effects of electrical actuation on the flight control actuation system (FCAS) architecture, and Pacelab SysArc software was used for design, modelling and analysis. As alternatives to the existing system, hybrid and all-electric models are built to a set of design guidelines with certain limitations. Findings Compared to the existing FCAS architecture model, 80 kg weight savings in the hybrid FCAS architecture model and 171 kg weight savings in the all-electric FCAS architecture model were observed. In terms of fuel consumption, it has been observed that there is 0.25% fuel savings in the hybrid FCAS architecture model, and 0.48% fuel savings in the all-electric FCAS architecture model compared to the existing FCAS architecture model at 3200 NM. Practical implications In line with the data obtained from this study, it is predicted that electrical actuation is more preferable in aircraft, considering its positive effects on weight and fuel consumption. Originality/value In this study, three different models were created: the existing FCAS architecture of a commercial transport aircraft, the hybrid FCAS architecture and the all-electric FCAS architecture. Hybrid and all-electric models are built according to a set of design guidelines, with certain limitations. Then, similar flight missions consisting of the same flight conditions are defined to analyse the effects of power consumption, weight, and fuel consumption comparatively.
dc.identifier.doi10.1108/AEAT-11-2021-0326
dc.identifier.endpage1683
dc.identifier.issn1748-8842
dc.identifier.issn1758-4213
dc.identifier.issue10
dc.identifier.orcid0000-0003-1278-4028
dc.identifier.scopus2-s2.0-85129295003
dc.identifier.scopusqualityQ2
dc.identifier.startpage1671
dc.identifier.urihttps://doi.org/10.1108/AEAT-11-2021-0326
dc.identifier.urihttps://hdl.handle.net/11508/53491
dc.identifier.volume94
dc.identifier.wosWOS:000782619100001
dc.identifier.wosqualityQ3
dc.indekslendigikaynakWeb of Science
dc.indekslendigikaynakScopus
dc.language.isoen
dc.publisherEmerald Group Publishing Ltd
dc.relation.ispartofAircraft Engineering and Aerospace Technology
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanı
dc.rightsinfo:eu-repo/semantics/closedAccess
dc.snmzKA_WoS_20260511
dc.subjectElectro-hydrostatic actuator (EHA)
dc.subjectElectro-mechanical actuator (EMA)
dc.subjectFlight control actuation system (FCAS)
dc.subjectMore electric aircraft (MEA)
dc.titlePerformance analysis of electrical flight control actuation system in a commercial transport aircraft
dc.typeArticle

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