Vibration analysis of composite turbopropellers using a nonlinear beam-type finite-element approach

DOI10.2514/3.10308zbMath0711.73127OpenAlexW2030895533MaRDI QIDQ3495835

J. B. Kosmatka, Peretz P. Friedmann

Publication date: 1989

Published in: AIAA Journal (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.2514/3.10308

zbMATH Keywords

mode shapesnatural frequencieslinear perturbationsHamilton's principlerotating bladefree vibration characteristicsgeometrically nonlinear behaviorarbitrary cross-sectional propertiesgenerally anisotropic material behaviorlarge pretwist anglesmoderate deflection theoryout-of-plane cross-section warpingprop-fansstraight beam-type finite elements

Mathematics Subject Classification ID

Rods (beams, columns, shafts, arches, rings, etc.) (74K10) Vibrations in dynamical problems in solid mechanics (74H45)

Related Items (6)

Finite-Element-Based Nonlinear Modal Reduction of a Rotating Beam with Large-Amplitude Motion ⋮ Asymptotic analysis of Timoshenko-like orthotropic beam with elliptical cross-section ⋮ Aeroelastic tailoring analysis for advanced turbo propellers with composite blades ⋮ Accurate reduced-order models for a simple rotor blade model using nonlinear normal modes. ⋮ Period Doubling Motions of a Nonlinear Rotating Beam at 1:1 Resonance ⋮ Vibration and flutter of stiff-inplane elastically tailored composite rotor blades

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