固体火箭发动机水下应用时的燃速特性分析

火箭发动机内真实的推进剂燃速往往由于高温高压难以测量。为探讨燃速对于工况的依赖性．对水下应用的固体火箭发动机试验器的试验结果用最小二乘法进行了辨识。引用三种燃速公式进行辨识，得到了一种新型推进剂稳态燃速模型参数的最优辨识值。结果表明：指数式的辨识结果得到的残差最小，指数式是描述该新型推进剂燃速规律的合理格式。

Identification of burning rate of propellant for solid rocket motor underwater

The actual burning rate of propellant is difficult to measure because of the high tem-perature and pressure of rocket motor. In order to research the dependency of the burning rate on working conditions,identification of the experiments results of rocket motor underwater by means of least square method was conducted. Three kinds of expressions were introduced and each of them was adopted to the identification process. The optimum identification solution of the steady burning rate model parameter was obtaine...