火箭发动机流场快速计算方法研究  

Investigation on Fast Numerical Simulation Methods of Rocket Engine Flow

作　　者：陈浩[1] 李晓轩[1] 杨依峰 杨天鹏 张昱煜[1] Chen Hao;Li Xiao-xuan;Yang Yi-feng;Yang Tian-peng;Zhang Yu-yu(Beijing Institute of Space Long March Vehicle,Beijing,100076)

机构地区：[1]北京航天长征飞行器研究所,北京100076

出　　处：《导弹与航天运载技术》2021年第6期83-86,共4页Missiles and Space Vehicles

摘　　要：为了获得适用于火箭发动机喷管迭代优化的流场快速计算方法,采用CFD方法从气体参数和计算区域2个方面研究了不同火箭发动机数值仿真方法所引入的偏差和计算效率的差异。研究发现,采用等效单组分气体和仅内流的计算方法可以在将计算效率分别提升2.5倍和14.5倍的同时保持计算精度。因此,从计算精度和计算效率2个方面进行综合考虑,建议在工程设计中采用仅内流的简化计算方法进行火箭发动机的推力评估。In order to obtain a fast flow field calculation method suitable for iterative optimization of rocket engine nozzle,different numerical simulation methods of rocket engine based on CFD have been investigated on gas model and computational area in deviation and efficiency.It is found that by using equivalent single component gas model and calculating internal flow only,the calculation efficiency can be improved by 2.5 times and 14.5 times respectively,while maintaining the calculation accuracy at the same time.Therefore,considering the calculation accuracy and efficiency,it is suggested to use the simplified calculation method of the internal flow only in the engineering design for the thrust evaluation of rocket engine.

关 键 词：数值仿真 火箭发动机 气体模型 计算区域 

分 类 号：V411.3[航空宇航科学与技术—航空宇航推进理论与工程]