固体发动机点火压强峰的CFD计算方法研究

Research on CFD calculation method for solid rocket motor ignition pressure peak

介绍了固体火箭发动机点火压强峰形成的原因,分析了固体发动机实测压强和预示压强产生偏差的因素,提出了一种工程适用的基于加质模型的计算流体力学(computational fluid dynamics,CFD)方法,能够较准确地预示固体火箭发动机点火压强峰,特别是大长径比类固体火箭发动机。通过对比典型发动机的理论计算结果和试验数据,发动机点火压强峰预示误差减小至10%以内,对于发动机结构安全设计和整体性能的优化设计都有重要的指导意义。

This paper introduces the causes of the formation of ignition pressure peak in solid rocket motor and analyzes the deviation factor between its measured pressure and the predicted pressure.A CFD(computational fluid dynamics)method based on the additive mass model is proposed to improve the accuracy of the prediction of the ignition pressure peak of solid rocket motor,especially for solid rocket motors with large aspect ratio.Comparison between the theoretical calculation results and test data of typical engines shows that this CFD method can reduce the prediction error of the engine ignition pressure peak to less than 10%.It contributes to the safety design of the engine structure and the optimal design of the overall performance.