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首页> 外文期刊>Journal of Spacecraft and Rockets >Experimental Characterization of Material Properties of Novel Silica/Polysiloxane Ablative
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Experimental Characterization of Material Properties of Novel Silica/Polysiloxane Ablative

机译:新型二氧化硅/聚硅氧烷烧蚀剂材料性能的实验表征

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摘要

This paper provides the details of the R&D of a new ablative material through a collaboration between The University of Texas at Austin and Techneglas LLC. The UHTR polysiloxane resin system is manufactured by Techneglas, based on a blend of polysiloxane chemistries. UHTR is used to fabricate silica fiber-reinforced composite materials by compression molding of prepreg. The objectives of this study are to process, fabricate, and experimentally characterize the physical, thermal, flammability, thermophysical, and ablation properties of the silica/UHTR composite. This silica/UHTR composite was compared with silica/phenolic fiber-reinforced polymers (FRPs) made in our lab as well as silica/phenolic (SC-1008) prepreg purchased commercially. The neat UHTR polysiloxane resin showed a higher char yield at 86.5% than the neat SC-1008 resin at 55.4%. Composites made from the UHTR resin showed exceptionally high char yields of 97.5, 96.7, and 95.8% for 35, 40, and 48 wt % samples, respectively. These composites showed superior recession rate, peak heat-soaked temperature, and mass loss rate during ablation testing using an oxy-acetylene test bed (OTB). Through-the-thickness thermal conductivity and specific heat capacity ranging from 50 to 600 degrees C were measured using laser flash analysis and differential scanning calorimetry.
机译:本文通过德克萨斯大学奥斯汀分校与Techneglas LLC的合作,提供了一种新型烧蚀材料的研发细节。 UHTR聚硅氧烷树脂系统是由Techneglas基于聚硅氧烷化学混合物制得的。 UHTR用于通过预浸料的压缩成型来制造二氧化硅纤维增强的复合材料。这项研究的目的是加工,制造和实验表征二氧化硅/ UHTR复合材料的物理,热,可燃性,热物理和烧蚀性能。将该二氧化硅/ UHTR复合材料与我们实验室制造的二氧化硅/酚醛纤维增强聚合物(FRP)以及市售的二氧化硅/酚醛(SC-1008)预浸料进行了比较。纯净的UHTR聚硅氧烷树脂在56.5%的情况下比纯净的SC-1008树脂显示出更高的炭收率(86.5%)。由UHTR树脂制成的复合材料对35、40和48 wt%的样品分别显示出97.5、96.7和95.8%的超高炭产率。这些复合材料在使用氧-乙炔测试台(OTB)进行的烧蚀测试中显示出优异的回缩率,峰值热浸温度和质量损失率。使用激光闪光分析和差示扫描量热法测量了厚度范围为50至600摄氏度的热导率和比热容。

著录项

  • 来源
    《Journal of Spacecraft and Rockets 》 |2018年第6期| 1401-1413| 共13页
  • 作者单位

    Univ Texas Austin, Polymer Nanocomposites Technol Lab, Dept Mech Engn, 204 E Dean Keeton St C2200, Austin, TX 78712 USA;

    Techneglas LLC, CTO, 2100 N Wilkinson Way, Perrysburg, OH 43551 USA;

    Univ Texas Austin, Dept Mech Engn, 204 E Dean Keeton St C2200, Austin, TX 78712 USA;

  • 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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