Elevated-temperature application of the IITRI compression test fixture for graphite/polyimide filmentary composites
B. Basava Raju, Charles J. Camarda, Paul A. Cooper, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Langley Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1979 - Technology & Engineering - 45 pages
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0.2-percent strain 06 Average 60 Width alignment pins Average eult 0.00 Average Gult B-staged behavior Carbon Fibre Reinforced composite at 589 composite at room composite materials Compression diagrams COMPRESSIVE PROPERTIES Effect of width elevated temperatures 589 ELEVATED-TEMPERATURE APPLICATION end blocks end tabs Experimental Regression analysis failure Fibre Reinforced Plastics FM-34 film adhesive gages glass/polyimide graphite/polyimide high as 589 HTS-2/PMR-15 composite IITRI test method laminate orientation Laminate thi0kness Langley Research Center load alignment matrix measured ultimate strength NASA nonlinear Number of plies percent Poisson's ratio polynomial replicate tests room and elevated room temperature Scatter of replicate shown in figure specimen bending specimen fabrication specimen width specimens failed standard error strain gages strength and stiffness strengths and initial TABLE tangent modulus Test 14 test procedure test specimen tested at room thermal thermocouples U.S. Customary Units ultimate compressive stresses Unidirectional Carbon Fibre vacuum variation in back-to-back