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A comparison of measured and calculated thermal stresses in a hybrid metal matrix composite spar cap elementA hybrid spar of titanium with an integrally brazed composite, consisting of an aluminum matrix reinforced with boron-carbide-coated fibers, was heated in an oven and the resulting thermal stresses were measured. Uniform heating of the spar in an oven resulted in thermal stresses arising from the effects of dissimilar materials and anisotropy of the metal matrix composite. Thermal stresses were calculated from a finite element structural model using anisotropic material properties deduced from constituent properties and rules of mixtures. Comparisons of calculated thermal stresses with measured thermal stresses on the spar are presented. It was shown that failure to account for anisotropy in the metal matrix composite elements would result in large errors in correlating measured and calculated thermal stresses. It was concluded that very strong material characterization efforts are required to predict accurate thermal stresses in anisotropic composite structures.
Document ID
19860002058
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Jenkins, J. M. (NASA Ames Research Center Moffett Field, CA, United States)
Taylor, A. H. (NASA Langley Research Center United States)
Sakata, I. F. (Lockheed California Co. Burbank, United States)
Date Acquired
September 5, 2013
Publication Date
September 1, 1985
Subject Category
Structural Mechanics
Report/Patent Number
NAS 1.15:86729
H-1289
NASA-TM-86729
Accession Number
86N11525
Funding Number(s)
PROJECT: RTOP 506-53-51
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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