某型运载火箭发射流场数值模拟

Numerical Simulation of Launching Flow Field of Certain Type Carrier Rocket

为了更真实地反映发动机尾焰流场的特征,以某型运载火箭为例,对其流场数值进行模拟。运用计算流体力学方法,以3维双喷管发动机为模型,考虑尾焰工况为氢气、一氧化碳、二氧化碳、水蒸气组成的混合气体,对运载火箭的发射流场进行模拟仿真,分析尾焰流的近场激波系结构和参数分布特征等。分析结果表明:混合气体情况下的流场各个参数分布和激波系结构与理论分析结果一致,地面上距离喷管中心1 m位置处受最大压力,大约为0.4 MPa,在两喷管中心温度最高,为2 700℃,为后续相关实验测量提供了参考和理论依据。

mIn order to truly reflect the characteristics of the flow field of the engine tail flame, take certain type carrier rocket as example, numerical simulated its flow field. Using computational fluid dynamics（CFD） method, as three dimensions dual nozzle engine for the model, considering the tail flame mixed gases composition including hydrogen, carbon monoxide, carbon dioxide and water vapor in working condition, simulate the flow field simulation of the carrier rocket launch, analyze the near-field plume flow shock wave system structure and the parameter distribution, etc. The analysis results show that each parameters distribution and shock wave structure under mixed gas are consistent with the theoretical analysis results, the distances from the center of the nozzle on the ground 1 m location by the maximum pressure, about 0.4 MPa, the highest temperature is in the center of the two nozzle which is about 2 700 ℃, provides reference for subsequent related experimental measurement and theoretical basis.