Postbuckling behavior of graphite/epoxy laminated cylindrical panels under axial compression
Conference
·
OSTI ID:143192
- Korea Advanced Institute of Science and Technology, Taejon (Korea, Republic of). Dept. of Aerospace Engineering
The buckling and postbuckling behavior of graphite/epoxy laminated cylindrical panels under axial compression are investigated by the nonlinear finite element method. For the finite element analysis, the updated Lagrangian formulation and the eight-node degenerated shell element are utilized. Improved load-increment and iteration strategies based on the deflection mode of panel are proposed for the incremental nonlinear finite element analysis along the postbuckling equilibrium path. Using the developed finite element program, the composite cylindrical panels are analyzed with various stacking sequences. The characteristics of buckling and postbuckling behavior is discussed in the view of load-carrying capacities and deformation. The behavior of axially compressed composite panels are largely dependent on the stacking sequence, and there exist some differences between the initial buckling loads and the postbuckling load-carrying capacities.
- OSTI ID:
- 143192
- Report Number(s):
- CONF-930246--; ISBN 0-87339-251-5
- Country of Publication:
- United States
- Language:
- English
Similar Records
Effects of local asymmetry on the buckling and postbuckling of composite laminates with a delamination
Scale effects in buckling, postbuckling, and crippling of graphite-epoxy Z-section stiffeners
Thermal postbuckling behavior of laminated composite plates
Book
·
Tue Jul 01 00:00:00 EDT 1997
·
OSTI ID:485093
Scale effects in buckling, postbuckling, and crippling of graphite-epoxy Z-section stiffeners
Thesis/Dissertation
·
Mon Dec 31 23:00:00 EST 1990
·
OSTI ID:7164385
Thermal postbuckling behavior of laminated composite plates
Journal Article
·
Wed Jun 01 00:00:00 EDT 1994
· AIAA Journal (American Institute of Aeronautics and Astronautics); (United States)
·
OSTI ID:6987917