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

作　　者：张棚 张赛文 杨渊 武丹 王亚洲 ZHANG Peng;ZHANG Saiwen;YANG Yuan;WU Dan;WANG Yazhou(Hubei Key Laboratory of Advanced Aerospace Propulsion Technology(System Design Institute of Hubei Aerospace Technology Academy),Wuhan 430040,China)

机构地区：[1]航天动力先进技术湖北省重点实验室(湖北航天技术研究院总体设计所),湖北武汉430040

出　　处：《武汉大学学报（工学版）》2021年第2期173-177,共5页Engineering Journal of Wuhan University

摘　　要：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.

关 键 词：固体火箭发动机 点火压强峰 侵蚀燃烧 内流场 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]