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Design, testing, and damage tolerance study of bonded stiffened composite wing cover panelsResults are presented from the application of damage tolerance criteria for composite panels to multistringer composite wing cover panels developed under NASA's Composite Transport Wing Technology Development contract. This conceptual wing design integrated aeroelastic stiffness constraints with an enhanced damage tolerance material system, in order to yield optimized producibility and structural performance. Damage tolerance was demonstrated in a test program using full-sized cover panel subcomponents; panel skins were impacted at midbay between stiffeners, directly over a stiffener, and over the stiffener flange edge. None of the impacts produced visible damage. NASTRAN analyses were performed to simulate NDI-detected invisible damage.
Document ID
19880045016
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Madan, Ram C.
(Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Sutton, Jason O.
(Douglas Aircraft Co. Long Beach, CA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
Structural Mechanics
Report/Patent Number
AIAA PAPER 88-2292
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
88A32243
Funding Number(s)
CONTRACT_GRANT: NAS1-17970
Distribution Limits
Public
Copyright
Other

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