利用火焰弯曲理论预测复合推进剂侵蚀函数的方法与应用

Approach and Application of Predicting Erosive Ratio of Composite Propellant Based on Flame Bending Theory

固体火箭推进剂的侵蚀函数目前还没有方便而有效的手段(无论理论方法还是实验手段)来获取,火焰弯曲理论能较好地揭示固体复合推进剂侵蚀燃烧现象,以此为基础,建立了火焰弯曲理论侵蚀函数方程,进一步求解得到随燃气流速变化的侵蚀函数。通过实例验证,该获取侵蚀函数的方法及获取的侵蚀函数具有较高的预示精度,满足工程计算要求,对于研究固体推进剂的侵蚀燃烧理论、获取固体火箭发动机侵蚀函数,以及提高固体火箭发动机内弹道预示精度,均具有重要的实际应用意义,该方法仅适用于AP复合推进剂。

There is no convenient and effective means(both theory and experimental means)to obtain erosive ratio(erosive function)of solid rocket propellant.The Flame Bending Theory(FBT)can better reveal the burning erosion phenomenon of solid propellant.On this basis,the FBT erosive ratio equation was established,and further the erosive function varying with the combustion gas flow was obtained from the equation.Through the examples,the method of obtaining erosive function and the obtained erosive function have very high prediction precision and meet the requirements of engineering calculations.The method has important practical application significance to research erosion combustion theory for solid rocket propellant,acquire erosive function of solid rocket motor,and improve the prediction accuracy of internal ballistics of solid rocket motor.This method is only suitable for AP composite propellants.