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Analytic Sensitivity and Approximation of Skin Buckling Constraints in Wing-Shape SynthesisExplicit expressions for terms of the stiffness and geometric stiffness matrices are derived for the buckling analysis of trapezoidal fiber composite wing skin panels. The formulation is based on Ritz analysis using simple polynomials, and leads to explicit expressions for the analytic sensitivities of the stiffness and geometric stiffness matrices with respect to layer thickness, fiber directions, and panel shape. Integration with wing box analysis using either the equivalent plate approach or the finite element method, makes it possible to obtain sensitivities of panel buckling constraints with respect to wing planform shape or locations of internal ribs and spars. The analytic sensitivities are used to construct approximations of panel buckling constraints for integrated wing/panel design synthesis.
Document ID
19990051026
Acquisition Source
Ames Research Center
Document Type
Reprint (Version printed in journal)
Authors
Livne, Eli
(Washington Univ. Seattle, WA United States)
Milosavljevic, Radomir
(Washington Univ. Seattle, WA United States)
Date Acquired
August 19, 2013
Publication Date
October 1, 1995
Publication Information
Publication: Journal of Aircraft
Publisher: American Institute of Aeronautics and Astronautics, Inc.
Volume: 32
Issue: 5
Subject Category
Structural Mechanics
Funding Number(s)
CONTRACT_GRANT: NAG2-723
Distribution Limits
Public
Copyright
Other

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