NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Buckling analysis for anisotropic laminated plates under combined inplane loadsThe buckling analysis presented considers rectangular flat or curved general laminates subjected to combined inplane normal and shear loads. Linear theory is used in the analysis. All prebuckling deformations and any initial imperfections are ignored. The analysis method can be readily extended to longitudinally stiffened structures subjected to combined inplane normal and shear loads.
Document ID
19750029615
Document Type
Conference Paper
Authors
Viswanathan, A. V.
Tamekuni, M.
Baker, L. L. (Boeing Commercial Airplane Co. Renton, Wash., United States)
Date Acquired
August 8, 2013
Publication Date
September 1, 1974
Subject Category
STRUCTURAL MECHANICS
Report/Patent Number
IAF PAPER 74-038
Funding Number(s)
CONTRACT_GRANT: NAS1-11879
Distribution Limits
Public
Copyright
Other