Volume 31 Issue 10
Oct.  2016
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Article Navigation >  Journal of Aerospace Power  > 2016  >  31(10): 2370-2375
XUE Jian-gang, GAO Xi-guang, FANG Guang-wu, ZHANG Sheng, SONG Ying-dong, WANG Fang. A damage constitutive model for needled CMCs composites and stress analysis of components[J]. Journal of Aerospace Power, 2016, 31(10): 2370-2375. doi: 10.13224/j.cnki.jasp.2016.10.009
Citation: XUE Jian-gang, GAO Xi-guang, FANG Guang-wu, ZHANG Sheng, SONG Ying-dong, WANG Fang. A damage constitutive model for needled CMCs composites and stress analysis of components[J]. Journal of Aerospace Power, 2016, 31(10): 2370-2375. doi: 10.13224/j.cnki.jasp.2016.10.009
shu

A damage constitutive model for needled CMCs composites and stress analysis of components

doi: 10.13224/j.cnki.jasp.2016.10.009

  • 1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;

  • 2. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;

  • 3. College of Chemical Engineering, Nanjing Forestry University, Nanjing 210037, China

  • Received Date: 2015-01-25
  • Publish Date: 2016-10-28
    Abstract
  • An anisotropic damage constitutive model for needled ceramic matrix composites was proposed based on continuum damage mechanics. The effects of both tensile damage and shear damage were considered in the model. The stress-strain curves of the material were obtained by tensile and shear tests and the parameters of the constitutive model obtained by curving-fitting. Then the model was written into commercial finite element software by user subroutine. Both calculated tensile and shear curves agreed with the test curves, and the maximum errors were 5.62% and 1.47% respectively. With both damage constitutive model and elastic model, an adjustment sheet of an aero-engine exhaust nozzle was calculated to analyze the mechanical response under complex aerodynamic load and temperature load. The stress distributions calculated by the two models were similar, but the value of damage constitutive model was obviously lower than that of the elastic model.

     

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