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首页> 外文期刊>Journal of Spacecraft and Rockets >Thermomechanical Behavior of Superalloy Thermal Protection System Under Aerodynamic Heating
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Thermomechanical Behavior of Superalloy Thermal Protection System Under Aerodynamic Heating

机译：气动加热下高温合金热保护系统的热力学行为

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摘要

This study investigated the thermomechanical behavior of a superalloy thermal protection system panel using a combination of experiments and numerical simulation. A superalloy thermal protection system panel was created by sandwiching a thermal insulation material and two superalloy plates with the support of spacer structures. The applied temperature profile was calculated from aerodynamic heating data. The thermal protection system panel was tested for three thermal cycles (approximately three missions). Thermal deformation of the thermal protection system panel was measured using a three-dimensional digital image correlation method. The results indicate that the presented thermal protection system panel provided good thermal protective performance under a thermal loading of 1023 K (750 degrees C) with a heat-shielding index of 78% in the steady-state condition. The crucial finding is the permanent deformation of the thermal protection system panel after the first thermal cycle test. The thermomechanical coupled simulation results reveal the occurrence of a permanent deformation due to the plastic deformation of the spacer supporting structure, which was also observed in this Paper's experiment. This study offers an indispensable understanding of the thermomechanical response of the thermal protection system panel, which is crucial for preventing damage to the thermal protection system panel and for modifying the structural design of the supporting structure in the thermal protection system panel.
机译：这项研究通过实验和数值模拟相结合的方法研究了高温合金热防护系统面板的热机械行为。通过将隔热材料和两个带有间隔结构支撑的超合金板夹在中间来创建超合金热保护系统面板。根据空气动力学加热数据计算出施加的温度曲线。对热保护系统面板进行了三个热循环测试（约三个任务）。使用三维数字图像相关方法测量热保护系统面板的热变形。结果表明，所提出的热防护系统面板在1023 K（750摄氏度）的热负荷下提供了良好的热防护性能，稳态条件下的热屏蔽指数为78％。关键的发现是在第一次热循环测试后热保护系统面板的永久变形。热力耦合模拟结果表明，由于垫片支撑结构的塑性变形而导致永久变形的发生，这在本文的实验中也可以观察到。这项研究对热防护系统面板的热机械响应提供了必不可少的理解，这对于防止损坏热防护系统面板和修改热防护系统面板中支撑结构的结构设计至关重要。

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  • 来源
    《Journal of Spacecraft and Rockets》 |2019年第5期|1432-1448|共17页
  • 作者

    Vinh Tung Le; Goo Nam Seo; Kim Jae Young;

  • 作者单位

    Konkuk Univ Dept Adv Technol Fus Coll Engn Smart Microsyst Res Lab Seoul 05029 South Korea;

    Agcy Def Dev Daejeon 305600 South Korea;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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