GOX /HTPB混合火箭发动机回归速率的数值模拟与实验研究

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2021-07-16 DOI:10.1109/ICMAE52228.2021.9522500

Zhongshu Wang, H. Tian

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引用次数: 0

摘要

本文建立了GOX /HTPB混合火箭发动机回归率的二维数值模拟模型。考虑了烟尘颗粒辐射热流对回归速率的影响，并将数值模拟结果与实验结果进行了比较。数值模拟研究表明，在不考虑烟尘颗粒辐射热流影响的情况下，回归速率为0.83mm/s。考虑烟尘颗粒辐射热流影响的回归速率为0.94mm/s，更接近试验回归速率1.06mm/s。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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Numerical Simulation and Experimental Investigation on Regression Rate of GOX /HTPB Hybrid Rocket Motor

In this paper, a two-dimensional numerical simulation model of the regression rate for GOX /HTPB hybrid rocket motor is established. The influence of the soot particle radiation heat flow on the regression rate is considered, and the numerical simulation results are compared with experimental results. Numerical simulation studies have shown that regression rate is 0.83mm/s when the influence of the soot particle radiation heat flow is not considered. The regression rate is 0.94mm/s when considering the influence of radiation heat flow of soot particles, which is closer to the test regression rate 1.06mm/s.

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2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE)

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