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  • STRUCTURAL MECHANICS  (3)
  • 1
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    Aeroelastic analysis for propellers - mathematical formulations and program user's manual (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Mathematical development is presented for a specialized propeller dedicated version of the G400 rotor aeroelastic analysis. The G400PROP analysis simulates aeroelastic characteristics particular to propellers such as structural sweep, aerodynamic sweep and high subsonic unsteady airloads (both stalled and unstalled). Formulations are presented for these expanded propeller related methodologies. Results of limited application of the analysis to realistic blade configurations and operating conditions which include stable and unstable stall flutter test conditions are given. Sections included for enhanced program user efficiency and expanded utilization include descriptions of: (1) the structuring of the G400PROP FORTRAN coding; (2) the required input data; and (3) the output results. General information to facilitate operation and improve efficiency is also provided.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-3729 , NAS 1.26:3729 , UTRC83-6
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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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 manual (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The 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.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-2638
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Aeroelastic characteristics of composite bearingless rotor blades (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Owing to the inherent unique structural features of composite bearingless rotors, various assumptions upon which conventional rotor aeroelastic analyses are formulated, are violated. Three such features identified are highly nonlinear and time-varying structural twist, structural redundancy in bending and torsion, and for certain configurations a strongly coupled low frequency bending-torsion mode. An examination of these aeroelastic considerations and appropriate formulations required for accurate analyses of such rotor systems is presented. Also presented are test results from a dynamically scaled model rotor and complementary analytic results obtained with the appropriately reformulated aeroelastic analysis.
    Keywords: STRUCTURAL MECHANICS
    Type: Annual National Forum of the American Helicopter Society; May 10, 1976 - May 12, 1976; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
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