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Aeroelastic analysis for helicopter rotor blades with time-variable, non-linear structural twist and multiple structural redundancy: Mathematical derivation and program user's manualThe differential equations of motion for the lateral and torsional deformations of a nonlinearly twisted rotor blade in steady flight conditions together with those additional aeroelastic features germane to composite bearingless rotors are derived. The differential equations are formulated in terms of uncoupled (zero pitch and twist) vibratory modes with exact coupling effects due to finite, time variable blade pitch and, to second order, twist. Also presented are derivations of the fully coupled inertia and aerodynamic load distributions, automatic pitch change coupling effects, structural redundancy characteristics of the composite bearingless rotor flexbeam - torque tube system in bending and torsion, and a description of the linearized equations appropriate for eigensolution analyses. Three appendixes are included presenting material appropriate to the digital computer program implementation of the analysis, program G400.
Document ID
19770003613
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Bielawa, R. L. (United Technologies Research Center East Hartford, CT, United States)
Date Acquired
September 3, 2013
Publication Date
October 1, 1976
Subject Category
Structural Mechanics
Report/Patent Number
NASA-CR-2638
Accession Number
77N10556
Funding Number(s)
CONTRACT_GRANT: NAS1-10960
PROJECT: DA PROJ. 1F1-61102-AH-45
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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