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<p>The sandwich structure with ceramic matrix composites (CMCs) skin and carbon form (CF) core is the ideal thermal structural components with excellent thermal protective and lightweight properties in hypersonic vehicles. However, the temperature gradient and mismatch of thermal conductivity between CMC skin and CF core result in the thermal stress in sandwich structures. Therefore, core material CF with matching thermal conductivity have become very important to prevent cracks and debonding of the sandwich structure. In this work, carbon nanotubes (CNTs) reinforced carbon foam composites with different microstructure were fabricated using simple phenolic resin foaming followed by CVI process. The prepared CF display a very low density of 0.075&#xa0;g/cm<sup>3</sup> and a relatively high compressive strength of 1.65&#xa0;MPa. By controlling the distribution position and content of CNTs the thermal conductivity of core materials CF/CNTs (4.93&#xa0;W·m<sup>− 1</sup>·K<sup>− 1</sup> which is ~ 13 times higher than that of CF) can be regulated to compatibility with CMCs skin (3.5 ~ 6.0&#xa0;W/m·K). And the thermal conductivity evolution mechanisms of the CF/CNTs from room temperature to 1200 ℃ were revealed. High interfacial thermal resistance by phonon scattering between the CF and CNTs blocks the solid conduction of materials at room temperature. With the increase of the temperature, radiative heat transfer between CF and CNTs becomes more violent and dominates the heat transfer path. The C/CMCs-CMCs sandwich structure was fabricated quickly by the in situ foaming method.</p>

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In situ construction of lightweight CF/CNTs with compatible thermal performance toward sandwich structures for hypersonic vehicles

  • 期刊论文

  • 发表日期：

    2026年1月26日

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  • Qian Wang,
  • Bo-Wen Chen,
  • De-Wei Ni,
  • Fu-Chen Liu,
  • Fei-Yan Cai,
  • Chun-Jing Liao,
  • Hong-Da Wang,
  • Yu-Sheng Ding,
  • Shao-Ming Dong

摘要

The sandwich structure with ceramic matrix composites (CMCs) skin and carbon form (CF) core is the ideal thermal structural components with excellent thermal protective and lightweight properties in hypersonic vehicles. However, the temperature gradient and mismatch of thermal conductivity between CMC skin and CF core result in the thermal stress in sandwich structures. Therefore, core material CF with matching thermal conductivity have become very important to prevent cracks and debonding of the sandwich structure. In this work, carbon nanotubes (CNTs) reinforced carbon foam composites with different microstructure were fabricated using simple phenolic resin foaming followed by CVI process. The prepared CF display a very low density of 0.075 g/cm3 and a relatively high compressive strength of 1.65 MPa. By controlling the distribution position and content of CNTs the thermal conductivity of core materials CF/CNTs (4.93 W·m− 1·K− 1 which is ~ 13 times higher than that of CF) can be regulated to compatibility with CMCs skin (3.5 ~ 6.0 W/m·K). And the thermal conductivity evolution mechanisms of the CF/CNTs from room temperature to 1200 ℃ were revealed. High interfacial thermal resistance by phonon scattering between the CF and CNTs blocks the solid conduction of materials at room temperature. With the increase of the temperature, radiative heat transfer between CF and CNTs becomes more violent and dominates the heat transfer path. The C/CMCs-CMCs sandwich structure was fabricated quickly by the in situ foaming method.