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Assessing the thermal safety of solid propellant charges based on slow cook-off tests and numerical simulations

机译：基于缓慢炊具测试和数值模拟评估固体推进剂电荷的热安全性

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摘要

A method is proposed to assess the thermal safety of solid propellant charges by measuring the tem-perature and pressure of propellant specimens during cook-off tests and determining the reaction kinet-ics. In this work, two propellants-ammonium perchlorate/hydroxy-terminated polybutadiene/aluminum (AP/HTPB/Al), and ammonium perchlorate/hydroxy-terminated polyether/aluminum (AP/HTPE/Al)-are taken as examples to demonstrate this method in detail. Specifically, by implementing two kinds of cook-off tests-viz., multipoint temperature monitoring, and combustion pressure measurement-the ther-mal reaction temperature before ignition and the combustion pressure after ignition of the two propel-lants were respectively determined. Then, the kinetic parameters of the thermal decomposition reaction model and the parameters of the combustion reaction model were numerically simulated and calibrated to achieve mathematical descriptions of the entire process of cook off of two solid propellant charges. On this basis, the technology of grid-node separation calculation was employed to simulate and predict the rupture of a solid rocket motor case, thereby quantitatively describing the severity of the cook-off reaction. The results demonstrate that, at a heating rate of 1 K min -1, the ignition positions of the two propellant charges in the solid rocket motor are located in the annular area where the side wall and the front of the casing are joined. Compared with those of the AP/HTPE/Al charge, the ignition time of the AP/HTPB/Al charge is longer (12,714 s for AP/HTPB/Al vs. 9701 s for AP/HTPE/Al), the temperature of the casing before ignition is higher (501.5 K for AP/HTPB/Al vs. 466.2 K for AP/HTPE/Al), the reaction after ignition is more intense, and the deformation of the casing is more serious. (C) 2021 The Combustion Institute. Published by Elsevier Inc. All rights reserved.
机译：提出了一种方法，通过在烤燃试验测量TEM-perature和推进剂试样的压力和确定反应KINET-ICS评估的固体推进剂装料的热安全性。在这项工作中，两个推进剂 - 过氯酸铵/羟基封端的聚丁二烯/铝（AP / HTPB / Al）和高氯酸铵/羟基封端的聚醚/铝（AP / HTPE / Al）的-are作为实施例来说明该方法详细。具体而言，通过实施2种烤燃测试 - 即，多点温度监测，和燃烧压力测量-的疗法-MAL反应温度的点火之前和两个推进-lants点火后燃烧压力分别确定。然后，该热分解反应模型的动力学参数和燃烧反应模型的参数进行了数值模拟和校准，以实现两个固体推进剂装料煮掉的整个过程的数学描述。在此基础上，网格节点的分离计算技术被采用来模拟和预测固体火箭发动机壳体的破裂，从而定量地描述烤燃反应的严重程度。结果表明，以1K min的加热速率-1，在固体火箭发动机两个推进剂装料点火位置位于在所述侧壁和所述外壳的前面接合的环形区域。与那些AP / HTPE / Al的电荷相比，AP / HTPB / Al的电荷的点火时间较长（12714个S代表AP / HTPB / Al的对比9701个S代表AP / HTPE / Al）等的温度点火前壳体是更高（对于AP / HTPB / Al的501.5ķ与466.2 K中AP / HTPE / Al）的，点火后的反应更强烈，并且所述壳体的变形更为严重。 （c）2021燃烧研究所。由elsevier Inc.保留所有权利发布。

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  • 来源
    《Combustion and Flame》 |2021年第6期|154-162|共9页
  • 作者

    Kou Yongfeng; Chen Lang; Lu Jianying; Geng Deshen; Chen Wei; Wu Junying;

  • 作者单位

    Beijing Inst Technol State Key Lab Explos Sci & Technol Beijing 100081 Peoples R China;

    Beijing Inst Technol State Key Lab Explos Sci & Technol Beijing 100081 Peoples R China;

    Beijing Inst Technol State Key Lab Explos Sci & Technol Beijing 100081 Peoples R China;

    Beijing Inst Technol State Key Lab Explos Sci & Technol Beijing 100081 Peoples R China;

    Beijing Inst Technol State Key Lab Explos Sci & Technol Beijing 100081 Peoples R China;

    Beijing Inst Technol State Key Lab Explos Sci & Technol Beijing 100081 Peoples R China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);美国《生物学医学文摘》(MEDLINE);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Solid motor; Propellant; Thermal safety; Cook-off test; Numerical simulation;

    机译：固体电机;推进剂;热安全;炊具测试;数值模拟;

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