由于火箭发动机的部分典型参数无法公开,这增加了性能分析研究的困难度。文中建立了一个通过部分公开参数获取其他未公开典型参数的参数辨识模型。本模型在火箭发动机各参数间关联关系的基础上,结合热力计算方法与一维等熵流动关系获取燃烧室组分、热力参数以及喷管流动参数,并采用模式搜索法对推进剂配比进行优化。最后,本模型对STAR 12GV型火箭发动机进行了估算,所获仿真结果与公开参数基本一致,符合工程应用标准。

Some typical parameters of the rocket thruster cannot be disclosed, which increases the difficulty of performance optimization.This work establishes a parameter identification model for obtaining other undisclosed typical parameters through partial disclosure parameters.Based on the correlation between various parameters of the rocket thruster, the model combines the thermal calculation method and the one-dimensional isentropic flow relationship to obtain the combustion chamber composition, thermal parameters and nozzle flow parameters, then applies the pattern search method to optimize the propellant ratio.Finally, the STAR 12GV rocket thruster is estimated by this model.Compared with the experimental results in the reference, it showed that this method meets the needs of engineering applications.