SEDL / STP / STP546-EB / STP35485S

A Correlation Study of Finite-Element Modeling for Vibrations of Composite Material Panels

Thornton, EA
Associate professor, Old Dominion University, Norfolk, Va.

Clary, RR
Aerospace engineer, NASA Langley Research Center, Hampton, Va.

Pages: 19    Published: Jan 1974

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Abstract

A correlation study has been made to evaluate the effectiveness of finite-element modeling for vibrations of composite material panels. The three types of composite material panels studied were: (1) Symmetrically laminated cross-ply panels, (2) unsymmetrically laminated cross-ply panels, and (3) a 1/6-scale sandwich wing model. Correlations of finite-element predictions for frequencies and vibration modes were made with Rayleigh-Ritz analyses and experimental data.

For the symmetrically laminated panels the finite-element representation predicted vibration modes very accurately. For the unsymmetrically laminated panels it was found that predictions using uncoupled finite-element plate bending elements did not give good agreement with experimental data. The constant-chord, swept-wing model was effectively analyzed by finite-element presentations using either sandwich elements or ribs and spars.