固体推进剂燃烧表面温度的预估

Method on predicting burning surface temperature of solid propellant

关键词:  固体推进剂火箭发动机  燃烧  表面温度  燃烧催化剂  预测  燃速调节剂

Key words:  Solid propellant rocket engine  combustion  Surface temperature  Combustion catalyst  Prediction  Burning rate modifier

摘要:

通过对燃烧表面附近气相产物的分析,建立了固体推进剂化学结构与燃烧表面温度(Ts)的对应关系。在一定假设和实验的基础上,使对应关系定量化,由此提出了预估推进剂燃烧表面温度的方法。由该预估方法计算的燃烧表面温度、及其随压强变化的规律都与实际情况基本一致。并进一步提出了燃烧表面温度与催化剂分解峰温(Tm)相匹配原则,作为推进剂燃烧催化剂选择的新原则。

Abstract:

A correlation between chemical structure and burning surface temperature(T_s)of solid propellant was conducted by analyzing gas-phase products nearby burning surface. The correlation was fixed quantified based on hypothesis and experimental research. A fresh method on how to predict burning surface temperature of solid propellants was demonstrated. Calculated T_s and T_s～p curve were corresponding to conclusions in practice. Furthermore,a matching principle between T_s and decomposition peak temperature(T_m)of catalysts was suggested. The matching principle was used to select combustion catalyst of solid propellant. Another new method of design burning rate of solid propellants was described.