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Volume 41 Issue 9
Sep.  2015
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Journal of Beijing University of Aeronautics and Astronautics  > 2015  >  41(9): 1714-1721.
LI Jinliang, GU Yizhuo, LI Min, et al. Curing method and temperature distribution of composites based on flexible electric heating film[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(9): 1714-1721. doi: 10.13700/j.bh.1001-5965.2014.0683(in Chinese)
Citation: LI Jinliang, GU Yizhuo, LI Min, et al. Curing method and temperature distribution of composites based on flexible electric heating film[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(9): 1714-1721. doi: 10.13700/j.bh.1001-5965.2014.0683(in Chinese)
shu

Curing method and temperature distribution of composites based on flexible electric heating film

doi: 10.13700/j.bh.1001-5965.2014.0683
  • 1.

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

  • 2. The 54th Research Institute of China Electronics Technology Group Corporation, Shijiazhuang 050081, China

  • Received Date: 04 Nov 2014
  • Publish Date: 20 Sep 2015
    Abstract
  • Low-cost curing is a challenging task for composite manufacturing, especially for large-scale part. Vacuum assisted resin infusion (VARI) molding process was employed to fabricate carbon fiber/epoxy composite laminate. A curing method using flexible electric heating film (FEHF) was developed. The effects of lay-up type of FEHF and temperature cycle on the uniformity of temperature and curing degree of composite were studied. The results show that splicing overlaying FEHF has the most uniform temperature distribution with 11℃ maximum temperature difference at constant temperature stage. The temperature uniformity is improved by 26.7% and 38.9% compared to the cases using overlapping overlaying and interval overlaying FEHF, respectively. In addition, adding isothermal temperature platform is useful to reduce temperature difference during heating process, but the final temperature difference and distribution are the same as the case without adding isothermal temperature platform. By means of splicing overlaying FEHF, large antenna carbon fiber/epoxy composite reflector skin was fabricated, and the glass transition temperature of the reflector skin is over 80℃, and the reflector tolerance is 0.7 mm (r.m.s.). It demonstrates that FEHF is a feasible way for curing large composite part.

     

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