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Ablation and Thermal Response Property Model Validation for Phenolic Impregnated Carbon Ablator

机译：酚醛浸渍碳烧蚀剂的烧蚀及热响应特性模型验证

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摘要

Phenolic impregnated carbon ablator was the heat-shieldmaterial for the Stardust probe and was considered as ancandidate heat-shield material for the Orion Crew Module. As part of the heat-shield qualification for Orion,nphysical and thermal properties were measured for newly manufactured material, including emissivity, heatncapacity, thermal conductivity, elemental composition, and thermal decomposition rates. Based on these properties,nan ablation and thermal-response model was developed for temperatures up to 3500 K and pressures up to 100 kPa.nThe model includes transversely isotropic and pressure-dependent thermal conductivity. In this work, modelnvalidation is accomplished by comparison of predictions with data frommany arcjet tests conducted over a range ofnstagnation heat flux and pressure from107 W=cm2nat 2.3 kPa to 1100 W=cm2nat 84 kPa.Over the entire range of testnconditions, model predictions compare well with measured recession, maximum surface temperatures, in-depthntemperatures, and char depth.
机译：酚醛浸渍碳烧蚀剂是用于星尘探针的隔热材料，被认为是猎户座机组的候选隔热材料。作为Orion隔热板鉴定的一部分，对新制造的材料的物理和热性能进行了测量，包括发射率，导热性，导热性，元素组成和热分解速率。基于这些特性，开发了温度高达3500 K，压力高达100 kPa的纳米烧蚀和热响应模型。n该模型包括横向各向同性和压力相关的热导率。在这项工作中，模型验证是通过将预测值与在一定范围的滞热通量和压力范围从107 W = cm2nat 2.3 kPa到1100 W = cm2nat 84 kPa进行的许多电弧喷射试验的数据进行比较而完成的。测量的衰退，最大表面温度，深度温度和炭深。

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  • 来源
    《Journal of Spacecraft and Rockets》 |2010年第5期|p.786-805|共20页
  • 作者

    Frank S. Milos; Yih-Kanq Chen;

  • 作者单位

    NASA Ames Research Center, Moffett Field, California 94035-1000;

  • 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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