Theoretical buckling loads of boron/aluminum and graphite/resin fiber-composite anisotropic plates /
Christos C. Chamis.

Description

Main Author

Chamis, C. C. (Christos C.)

Related Names

United States. National Aeronautics and Space Administration.
Lewis Research Center.

Language(s)

English

Published

Washington, D.C. : National Aeronautics and Space Administration ; 1971.

Subjects

Anisotropy.
Fibrous composites.
Composite materials.
Aluminum.
Boron.
Plates (Engineering)

Summary

Theoretical results are presented for the buckling of anisotropic plates. The plates are subjected to simple and combined in-plane loading. The plates are made from fiber composite material of boron/aluminum or high-modulus graphite/resin. The results are presented in nondimensional form as buckling load against fiber orientation angle for various plate aspect ratios. The results indicate that buckling loads of boron/aluminum plates are independent of fiber direction if the plate aspect ratios are greater than about 1, and moderately dependent when this ratio is less than about 1. In addition, the results indicate that the buckling loads are independent of aspect ratio for plates with aspect ratios greater than about 2. Boron/ aluminum composite plates can resist buckling loads more efficiently than graphite/resin composites on a specific buckling stress basis. The numerical algorithm and a listing of the computer code used to obtain the results are included.

Physical Description

36 p. : ill. ; 28 cm.

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