NDLI: Computational procedures for postbuckling of composite shells

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Computational procedures for postbuckling of composite shells

Content Provider	NASA Technical Reports Server (NTRS)
Author	Stanley, G. M. Felippa, Carlos A.
Copyright Year	1989
Description	A recently developed finite-element capability for general nonlinear shell analysis, featuring the use of three-dimensional constitutive equations within an efficient resultant-oriented framework, is employed to simulate the postbuckling response of an axially compressed composite cylindrical panel with a circular cutout. The problem is a generic example of modern composite aircraft components for which postbuckling strength (i.e., fail-safety) is desired in the presence of local discontinuities such as holes and cracked stiffeners. While the computational software does a reasonable job of predicting both the buckling load and the qualitative aspects of postbuckling (compared both with experiment and another code) there are some discrepancies due to: (1) uncertainties in the nominal layer material properties, (2) structural sensitivity to initial imperfections, and (3) the neglect of dynamic and local material delamination effects in the numerical model. Corresponding refinements are suggested for the realistic continuation of this type of analysis.
File Size	1167218
Page Count	21
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19890015271
Archival Resource Key	ark:/13960/t3gx96t0x
Language	English
Publisher Date	1989-05-01
Access Restriction	Open
Subject Keyword	Structural Mechanics Aircraft Construction Materials Shells Structural Forms Computerized Simulation Shell Theory Computer Programs Finite Element Method Computation Predictions Nonlinearity Fuselages Composite Structures Buckling Loads Forces Structural Analysis Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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