针对固体火箭发动机改性双基固体推进剂静态燃速和动态燃速存在差异的普遍现象，分析了影响固体推进剂燃速的主要因素，提出基于最小二乘法固体火箭发动机装药动态燃速辨识方法。通过辨识的动态燃速计算得到的理论计算压强曲线与测试压强曲线对比分析可知，该方法提高了理论计算模型的预示精度，具有较强的工程应用价值。
Aiming at the common phenomenon that the static burning rate and the dynamic burning rate of modified double-base propellant for solid rocket motor were different. The main factors affecting the burning rate of solid propellant were analyzed. A method identifying the dynamic burning rate of solid rocket motor based on least square method is proposed. Comparisons between theoretical pressure curves calculated by identifying dynamic burning rate and test pressure curves, which show that this method improves the prediction accuracy of theoretical calculation model and has strong engineering application value.
2020,42(2): 181-184 收稿日期：2019-12-17
DOI：10.3404/j.issn.1672-7649.2020.02.035
分类号：V512
作者简介：刘宗魁(1987-),男,助理工程师,主要从事潜载导弹水下发射技术研究
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