首页> 外文期刊>Journal of Spacecraft and Rockets >Fundamental Modeling and Thermal Performance Issues for Metallic Thermal Protection System Concept
【24h】

Fundamental Modeling and Thermal Performance Issues for Metallic Thermal Protection System Concept

机译:金属热保护系统概念的基本建模和热性能问题

获取原文
获取原文并翻译 | 示例
           

摘要

A study was performed to develop an understanding of the key factors that govern the performance of metallic thermal protection systems for reusable launch vehicles. A current advanced metallic thermal protection system concept was systematically analyzed to discover the most important factors governing its thermal performance. A large number of relevant factors that influence the thermal analysis and thermal performance system were identified and quantified. Detailed finite element models were developed for predicting the thermal performance of design variations of the metallic thermal protection system concept mounted on a simple, unstiffened structure. The computational models were also used, in an automated iterative procedure, for sizing the metallic thermal protection system to maintain the structure below a specified temperature limit. A statistical sensitivity analysis method, based on orthogonal matrix techniques used in robust design, was used to quantify and rank the relative importance of the various modeling and design factors considered in this study. Thermal performance was shown to be sensitive to several analytical assumptions that should be chosen carefully. Of the design factors studied, the heat capacity of the underlying structure was found to have the greatest effect on thermal performance. Therefore the structure and thermal protection system should be designed concurrently.
机译:进行了一项研究,以了解对支配可重复使用运载火箭的金属热保护系统性能的关键因素的理解。系统分析了当前先进的金属热保护系统概念,以发现控制其热性能的最重要因素。识别并量化了影响热分析和热性能系统的大量相关因素。开发了详细的有限元模型,以预测安装在简单,不加劲的结构上的金属热保护系统概念的设计变型的热性能。该计算模型还用于自动迭代过程中,用于确定金属热保护系统的尺寸,以将结构保持在指定的温度极限以下。基于在稳健设计中使用的正交矩阵技术的统计敏感性分析方法用于量化和排名本研究中考虑的各种建模和设计因素的相对重要性。结果表明,热性能对应谨慎选择的几个分析假设敏感。在研究的设计因素中,发现底层结构的热容对热性能的影响最大。因此,结构和热保护系统应同时设计。

著录项

  • 来源
    《Journal of Spacecraft and Rockets》 |2004年第2期|p.195-206|共12页
  • 作者

    Max L. Blosser;

  • 作者单位

    NASA Langley Research Center, Hampton, Virginia 23681;

  • 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
  • 中图分类 航空;
  • 关键词

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱:kefu@zhangqiaokeyan.com

京公网安备:11010802029741号 ICP备案号:京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有
  • 客服微信

  • 服务号