固体火箭发动机比冲估算及界面程序实现

Solid Rocket Engine Specific Impulse Estimation Algorithm and Interface Program Realization

依据某推进剂热力计算结果和基于FLUENT软件平台的固体火箭发动机燃烧室和喷管两相流流场仿真得到的相关参数,根据比冲计算的相关理论,利用MATLAB图形用户界面(Graphical User Interface,GUI)软件编制了发动机比冲预估算程序,利用该程序对某型号固体火箭发动机的比冲进行了预估。预估结果与实验值对比表明,该程序可以对发动机比冲进行较准确和快速的估算。

According to a certain propellant thermal calculation results,FLUENT software simulation calculation results of two-phase flow field in the solid rocket engine combustion chamber and nozzle and the related theory for prediction of specific impulse,the solid rocket engine specific impulse prediction program is compiled.Some solid rocket engine specific impulse is predicted by using this program.Compared with the experimental values,the results show the program presented is reliable and the method is rapid for the estimation of solid rocket engine specific impulse.