Buckling of laminated composite plates and shell panels. Final report, 20 November 1980-20 January 1985

Technical Report · Sat Jun 01 04:00:00 EDT 1985

OSTI ID:6085178

Leissa, A W

This work summarizes the technical literature dealing with buckling and post-buckling behavior of laminated composite plates and shell panels. Emphasis is given to modern materials used in the aerospace industry having fiber-matrix constituents (e.g., glass-epoxy, boron-epoxy, graphite-epoxy, boron-aluminum), but other applications are also considered (e.g., plywood, paperboard). Geometric configurations taken up are either flat (plates) or cylindrically curved (shells), and have rectangular planform. All possible types of loading conditions and edge constraint conditions are considered. Both symmetrically and unsymmetrically laminated configurations are included, with symmetrical laminates represented by orthotropic or anisotropic plate or shell theory. Complicating effects dealt with include: internal holes, shear deformation, sandwich plates with soft cores, local instability, inelastic materials, hygrothermal effects and stiffeners. Approximately 400 references are used. Extension numerical results are presented in graphical and tabular form. Both theoretical and experimental results are summarized. Keywords: Vibrations; Unsymmetric laminates. (Author)

• Research Organization: Ohio State Univ. Research Foundation, Columbus (USA)
• OSTI ID: 6085178
• Report Number(s): AD-A-162723/1/XAB; OSURF-762513/713464
• Country of Publication: United States
• Language: English

Related Subjects

36 MATERIALS SCIENCE
360303* -- Composite Materials-- Mechanical Properties-- (-1987)
AEROSPACE INDUSTRY
BORON
BUCKLING
COMPOSITE MATERIALS
DEFORMATION
DOCUMENT TYPES
ELEMENTS
FIBERS
GLASS
INDUSTRY
MATERIALS
MATRIX MATERIALS
MECHANICAL PROPERTIES
PANELS
PLATES
REVIEWS
SEMIMETALS
SHEAR PROPERTIES
SYMMETRY