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Temperature effect on stress concentration around circular hole in a composite material specimen representative of X-29A forward-swept wing aircraftThe theory of anisotropic elasticity was used to evaluate the anisotropic stress concentration factors of a composite laminated plate containing a small circular hole. This advanced composite was used to manufacture the X-29A forward-swept wing. It was found for composite material, that the anisotropic stress concentration is no longer a constant, and that the locations of maximum tangential stress points could shift by changing the fiber orientation with respect to the loading axis. The analysis showed that through the lamination process, the stress concentration factor could be reduced drastically, and therefore the structural performance could be improved. Both the mixture rule approach and the constant strain approach were used to calculate the stress concentration factor of room temperature. The results predicted by the mixture rule approach were about twenty percent deviate from the experimental data. However, the results predicted by the constant strain approach matched the testing data very well. This showed the importance of the inplane shear effect on the evaluation of the stress concentration factor for the X-29A composite plate.
Document ID
19890005085
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Yeh, Hsien-Yang (California State Univ. Long Beach, CA, United States)
Date Acquired
September 5, 2013
Publication Date
August 1, 1988
Subject Category
Structural Mechanics
Report/Patent Number
NASA-CR-179439
H-1514
NAS 1.26:179439
Accession Number
89N14456
Funding Number(s)
CONTRACT_GRANT: NGT-05-020-412
PROJECT: RTOP 533-02-5
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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