Elevator flutter involving two tabs

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dc.contributor.author E. G. Broadbent en_US
dc.contributor.author Mary Clarke en_US
dc.date.accessioned 2014-10-21T15:55:08Z
dc.date.available 2014-10-21T15:55:08Z
dc.date.issued 1954 en_US
dc.identifier.other ARC/R&M-3210 en_US
dc.identifier.uri https://reports.aerade.cranfield.ac.uk/handle/1826.2/3781
dc.description.abstract An account is given of a theoretical flutter investigation in connection with an accident to a Sea Venom aircraft. The investigation covers both symmetric and antisymmetric flutter of the tailplane-elevator-tab system. The main (symmetric) calculations include six degrees of freedom, comprising three structural modes and movements of elevator, spring-tab and trim-tab respectively. The parameters that are varied include elevator mass-balance, position and magnitude of mass-balance on each tab independently, structural damping and stiffness of the tab circuits, chord and mass of the trim-tab, and flexibility of the elevator mass-balance attachments. The investigation shows the symmetric flutter to be a probable cause of the accident and confirms the efficacy of the remedial measures adopted, which consisted of modifications to the tab mass-balances combined with a reduction in chord and inertia of the trim-tab. Several points of general interest are discussed. en_US
dc.relation.ispartofseries Aeronautical Research Council Reports & Memoranda en_US
dc.title Elevator flutter involving two tabs en_US

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