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Volume 39 Issue 8
Aug.  2013
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Journal of Beijing University of Aeronautics and Astronautics  > 2013  >  39(8): 1037-1041.
Ma Yue, Zhao Haitao, Han Haijun, et al. Stability on the damping capacity and microstructure of the high strength damping aluminum alloy[J]. Journal of Beijing University of Aeronautics and Astronautics, 2005, 31(02): 121-124. (in Chinese)
Citation: Zhang Jikui, Ma Zhiyang, Li Xuemei, et al. Numerical simulation of cure deformation of composite taper shell with thermal protection layer[J]. Journal of Beijing University of Aeronautics and Astronautics, 2013, 39(8): 1037-1041. (in Chinese)
shu

Numerical simulation of cure deformation of composite taper shell with thermal protection layer

  • 1.

    School of Aeronautics Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • 2. Aerospace Research Institute of Materials and Processing Technology, Beijing 100076, China

  • Received Date: 30 Aug 2012
  • Rev Recd Date: 26 Nov 2012
  • Publish Date: 30 Aug 2013
    Abstract
  • A three-dimensional finite element model was developed to simulate and predict the cure deformation during the winding processing of a composite taper shell with thermal protection layers. According to the results of numerical simulation, the first cause of the shell's cure deformation was the thermal expansion coefficient difference between protection material and structural material which lay on outer layers and inner layers respectively. Meanwhile, this cure deformation can be controlled effectively by adding the middle layer between outer layers and inner layers, which reduced about 20% deformation by using nitrile rubber as the middle layer's material. The effects of other influence factors were also discussed: cure deformation was increased by improving the middle layer's modulus and decreased slightly by increasing the middle layer's thickness; the relief of winding tension, to some degree, had an impact on deformation, and larger tension leads to higher deformation.

     

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    • References(14)
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