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现代固体推进剂在稳态和振荡燃烧时,其燃面上方的化学反应界面层传热和流体力学性能,曾庄1977年的一篇博士论文中提出。自那以后,燃烧和推进方面的进展,并没有得到该论文所给模型(SOCSP模型)预期的效果。本研究试图给出一侧面燃烧药型的发动机轴向燃烧不稳定真实原因的新假说,来显示SOCSP模型的效果。对提出的新“星状火焰”假说进行讨论。考虑到目前的发展趋势,决定把计算机所得SOCSP模型的数值结果(基于“计算机推进剂”)作为“星状火焰”理论发展的基础。本文结尾推荐了一套对现代火箭设计者和实验人员有用的无量纲数据组,这是本项研究的副产物。
Modern steady propellant solid-state and oscillatory combustion, the combustion surface of the chemical reaction layer above the heat transfer and fluid mechanical properties, Zengzhuang in a doctoral thesis in 1977 proposed. Since then, progress on combustion and propulsion has not been matched by the expected effect of the model (SOCSP model) presented in this paper. This study attempts to give a new hypothesis about the real cause of axial combustion instability of a side-fired propellant to show the effect of the SOCSP model. Discuss the proposed new “star flame” hypothesis. Considering the current development trend, we decided to take the numerical results of computer-generated SOCSP model (based on “computer propellant”) as the basis for the development of the “star flame” theory. This concludes with a set of dimensionless data sets that are of use to modern rocket designers and experimenters as a byproduct of this study.