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Concepts for improving the damage tolerance of composite compression panelsThe residual strength of specimens with damage and the sensitivity to damage while subjected to an applied inplane compression load were determined for flatplate specimens and blade-stiffened panels. The results suggest that matrix materials that fail by delamination have the lowest damage tolerance capability. Alternate matrix materials or laminates which are transversely reinforced suppress the delamination mode of failure and change the failure mode to transverse shear crippling which occurs at a higher strain value. Several damage-tolerant blade-stiffened panel design concepts are evaluated. Structural efficiency studies conducted show only small mass penalties may result from incorporating these damage-tolerant features in panel design. The implication of test results on the design of aircraft structures was examined with respect to FAR requirements.
Document ID
19840010610
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rhodes, M. D. (NASA Langley Research Center Hampton, VA, United States)
Williams, J. G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
February 1, 1984
Subject Category
Structural Mechanics
Report/Patent Number
NASA-TM-85748
NAS 1.15:85748
Report Number: NASA-TM-85748
Report Number: NAS 1.15:85748
Meeting Information
Meeting: Conf. on Fibrous Composites in Structural Design
Location: New Orleans, LA
Country: United States
Start Date: January 1, 1981
Accession Number
84N18678
Funding Number(s)
PROJECT: RTOP 534-06-23
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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