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Generator Configuration for a Helicopter Quadruplex Electric Tail Rotor

Research output: Contribution to journalArticle

Original languageEnglish
Pages (from-to)4471-4474
Number of pages4
JournalJournal of Engineering
Volume2019
Issue number17
Early online date12 Apr 2019
DOIs
DateAccepted/In press - 30 Jul 2018
DateE-pub ahead of print - 12 Apr 2019
DatePublished (current) - 1 Jun 2019

Abstract

With the move to more electric aircraft, a key area of investigation is the development of commercially viable systems which are reliable, efficient, low mass, and are compatible and commensurate with the power and multiplex requirements of current and future aircraft. In rotorcraft, the pace of adopting more electric systems, to replace conventional mechanical and hydraulic ones, say, is perceived as being much lower than in fixed wing aircraft. However, recently there has been growing evidence to suggest that a quadruplex electric tail rotor is a technically viable solution. This paper shows the methodology to support the most reliable configuration of the four independent generators required to power such a quadruplex tail rotor drive, and takes account of the failure severity due to power loss in each independent channel, target reliability setting and supporting reliability analyses. The conclusions drawn support a particular hybrid series-parallel configuration of generators, with identification of further work related to the gearbox reliabilities which support the reliability attainment for the configuration.

    Research areas

  • More electric aircraft, helicopter tail rotor, quadruplex system, generator configuration, reliability

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    Rights statement: This is the final published version of the article (version of record). It first appeared online via IET at https://digital-library.theiet.org/content/journals/10.1049/joe.2018.8233 . Please refer to any applicable terms of use of the publisher.

    Final published version, 2 MB, PDF-document

    Licence: CC BY-ND

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