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首页> 外文期刊>International journal of aerospace engineering >Precise Design of Solid Rocket Motor Heat Insulation Layer Thickness under Nonuniform Dynamic Burning Rate
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Precise Design of Solid Rocket Motor Heat Insulation Layer Thickness under Nonuniform Dynamic Burning Rate

机译：动态燃速不均匀的固体火箭发动机绝热层厚度的精确设计

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摘要

With the purpose of obtaining optimal designs of the heat insulating layers in solid rocket motors, we have proposed a numerical approach to compute the ideal thickness of the heat insulating layer. The proposed method is compatible with solid rocket motors that have any shape and any manner of erosion. The nonuniform dynamic burning rate is taken into consideration to achieve higher accuracy. A high-performance code is developed that uses triangular geometry as an input to allow exchanging data from any CAD platform. An improved geometric intersection algorithm is developed to generate the required sampling points, saving 35% computation time compared to its open source equivalent. Parallel computing technology is utilized to further improve the performance. All operations of the proposed approach can be executed automatically by programs, eliminating the manual work of gathering data from CAD software in the traditional approach. Validation data shows that the proposed approach saves 3.85% of the mass compared to the ordinary design approach. Performance profiling shows that the implemented code operates within 5 seconds, which is much faster than the unoptimized open source version.
机译：为了获得固体火箭发动机中隔热层的最佳设计，我们提出了一种数值方法来计算隔热层的理想厚度。所提出的方法与具有任何形状和任何形式的腐蚀的固体火箭发动机兼容。为了获得更高的精度，要考虑不均匀的动态燃烧速率。开发了一种高性能的代码，该代码使用三角形几何图形作为输入，以允许从任何CAD平台交换数据。开发了一种改进的几何相交算法来生成所需的采样点，与之相比，它节省了35％的计算时间。利用并行计算技术来进一步提高性能。所提出方法的所有操作都可以由程序自动执行，从而省去了传统方法中从CAD软件收集数据的手动工作。验证数据表明，与普通设计方法相比，该方法节省了质量的3.85％。性能分析表明，已实现的代码在5秒钟内运行，这比未优化的开源版本要快得多。

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  • 来源
    《International journal of aerospace engineering》 |2019年第1期|5789430.1-5789430.13|共13页
  • 作者

    Wei Ran; Bao Futing; Liu Yang; Hui Weihua;

  • 作者单位

    Northwestern Polytech Univ, Sch Astronaut, Sci & Technol Combust Internal Flow & Thermo Stru, Xian 710072, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sch Astronaut, Sci & Technol Combust Internal Flow & Thermo Stru, Xian 710072, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sch Astronaut, Sci & Technol Combust Internal Flow & Thermo Stru, Xian 710072, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sch Astronaut, Sci & Technol Combust Internal Flow & Thermo Stru, Xian 710072, Shaanxi, Peoples R China;

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