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Preliminary design of composite wing-box structures for global damage toleranceA procedure is presented that incorporates the influence of potential global damage conditions into the design process for minimum-mass wing-box structures. The procedure is based on mathematical-programming optimization techniques. Material-strength, minimum-gage, and panel-buckling constraints are introduced by penalty functions, and Newton's method with approximate second derivatives of the penalty terms is used as the search algorithm to obtain minimum-mass designs. A potential global damage condition is represented by a structural model with the damaged components removed. Example minimum-mass designs are obtained that simultaneously satisfy the constraints of the damaged and undamaged configurations of both graphite-epoxy and aluminum wing-box structural models. These examples are designed with and without the influence of potential damage conditions, and results indicate that for equal mass cases the residual strength of a damaged structure is higher when the influence of potential damage is properly included in the design from the outset. Results of these examples also identify the minimum structural mass increase required to increase residual strength levels.
Document ID
19800050879
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Starnes, J. H., Jr.
(NASA Langley Research Center Structures and Dynamics Div., Hampton, Va., United States)
Haftka, R. T.
(Illinois Institute of Technology Chicago, Ill., United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1980
Subject Category
Structural Mechanics
Report/Patent Number
AIAA PAPER 80-0755
Meeting Information
Meeting: Structures, Structural Dynamics, and Materials Conference
Location: Seattle, WA
Start Date: May 12, 1980
End Date: May 14, 1980
Accession Number
80A35049
Funding Number(s)
CONTRACT_GRANT: NAG1-5
Distribution Limits
Public
Copyright
Other

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