NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Influence of geometric nonlinearities on skin-stiffener interface stressesA method for computing skin-stiffener interface stresses in stiffened composite panels is developed. Both geometrically linear and nonlinear analyses are considered. Particular attention is given to the flange termination region where stresses are expected to exhibit unbounded characteristics. The method is based on a finite-element analysis and an elasticity solution. The results indicate that the inclusion of geometric nonlinearities is very important for an accurate determination of the interface stresses. Membrane flattening of the panel tends to reduce the tendency of the stiffener to separate.
Document ID
19880044958
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cohen, D.
(Hercules Aerospace Co. Magna, UT, United States)
Hyer, M. W.
(Virginia Polytechnic Institute and State University Blacksburg, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
Structural Mechanics
Report/Patent Number
AIAA PAPER 88-2217
Meeting Information
Meeting: Structures, Structural Dynamics and Materials Conference
Location: Williamsburg, VA
Country: United States
Start Date: April 18, 1988
End Date: April 20, 1988
Sponsors: Structures
Accession Number
88A32185
Funding Number(s)
CONTRACT_GRANT: NAG1-343
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available