Abstract: Based on the solid propellant burning rate formula, a new method for the combustion time determination during the data treatment in solid rocket motor firing test was studied with a method of numerical integration and interpolation. The method was adopted in the development of ignition device, the result shows that it is scientific, correct and superiority.

Key words: Solid propellant rocket engine;Engine combustion time;Experimental data;Analysis method

摘要： 以固体推进剂燃速公式为基础 ,采用计算力学中的数值积分及插值法 ,并利用计算机技术 ,研究了用燃烧室药柱的实际肉厚 ,确定固体火箭发动机试验曲线中燃烧时间的新方法。在点火发动机中应用的结果表明 ,此方法解决了试验曲线数据处理结果散布范围较大的问题 ,提高了燃速预估的准确性。

关键词: 固体推进剂火箭发动机;发动机燃烧时间;实验数据;分析方法