BUCKDEL v 0.9 users and theory manuals :
buckling and delamination analysis of stiffened laminated plates /
D.S. Pipkins, S.N. Atluri.

Description

Main Author

Pipkins, Daniel S.

Related Names

Atluri, Satya N., author.
Wright Laboratory (Wright-Patterson Air Force Base, Ohio)

Language(s)

English

Published

Wright-Patterson Air Force Base, Ohio : Flight Dynamics Directorate, Wright Laboratory, Air Force Materiel Command, United States Air Force, 1996.

Subjects

Composite materials > Composite materials / Delamination.
Buckling (Mechanics)

Summary

BUCKDEL, performs geometrically nonlinear analysis of stiffened laminated composite plates with and without delaminations. BUCKDEL allows the user to perform: a linear static solution; a linear buckling (eigenvalue) analysis; and a nonlinear post-buckling analysis through both limit and bifurcation points. There are two finite elements in BUCKDEL; a quasi-conforming triangular laminated plate element based on a refined first order shear theory with seven degrees of freedom per node and a fiber reinforced beam element with seven degrees of freedom per node. The behavior of all materials is assumed to be linearly elastic. The multi-domain modeling method is used for the analysis of laminated plates containing delaminations. In this model, the delaminate, base and the undelaminate are modeled as 3 distinct. On the delamination front, Mindlin's deformation assumption is applied to obtain the relationship between the displacements in the delaminate, base and undelaminate.

Note

"Final report for the period September 1995 - March 1996."
"April 1996."

Physical Description

50 pages : illustrations ; 28 cm.

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