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Optimal Design of Grid-Stiffened Panels and Shells With Variable CurvatureA design strategy for optimal design of composite grid-stiffened structures with variable curvature subjected to global and local buckling constraints is developed using a discrete optimizer. An improved smeared stiffener theory is used for the global buckling analysis. Local buckling of skin segments is assessed using a Rayleigh-Ritz method that accounts for material anisotropy and transverse shear flexibility. The local buckling of stiffener segments is also assessed. Design variables are the axial and transverse stiffener spacing, stiffener height and thickness, skin laminate, and stiffening configuration. Stiffening configuration is herein defined as a design variable that indicates the combination of axial, transverse and diagonal stiffeners in the stiffened panel. The design optimization process is adapted to identify the lightest-weight stiffening configuration and stiffener spacing for grid-stiffened composite panels given the overall panel dimensions. in-plane design loads, material properties. and boundary conditions of the grid-stiffened panel or shell.
Document ID
20010059179
Acquisition Source
Langley Research Center
Document Type
Reprint (Version printed in journal)
Authors
Ambur, Damodar R.
(NASA Langley Research Center Hampton, VA United States)
Jaunky, Navin
(Eagle Aeronautics, Inc. Newport News, VA United States)
Date Acquired
August 20, 2013
Publication Date
January 1, 2001
Publication Information
Publication: Composite Structures
Publisher: Elsevier Science Ltd.
Volume: 52
ISSN: 0263-8223
Subject Category
Aircraft Design, Testing And Performance
Distribution Limits
Public
Copyright
Other

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