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Impact of the Surface Morphology on the Combustion of Simulated Solid Rocket Motor

机译：表面形态对模拟固体火箭发动机燃烧的影响

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摘要

An advanced and intensive computational solution development is integrated with an asymptotic technique, to examine the impact of the combustion surface morphology on the generated rotational flow field in a solid rocket chamber with wide ranges of forcing frequencies. The simulated rectangular chamber is closed at one end and is open at the aft end. The upper and lower walls are permeable to allow steady and unsteady injected air to generate internal flow mimicking the flow field of the combustion gases in real rocket chamber. The frequencies of the unsteady injected flow are chosen to be very close or away from the resonance frequencies of the adapted chamber. The current study accounts for a wide range of wave numbers that reflect the complexity of real burning processes. Detailed derivation for Navier-Stokes equations at the four boundaries of the chamber is introduced in the current study. Qualitative comparison is performed with recent experimental work carried out on a two-inch hybrid rocket motor using a mixture of polyethylene and aluminum powder. The higher the percentage of aluminum powder in the mixture, the more the corrugations of the combustion surface. This trend is almost similar to the computational and analytical results of a simulated solid rocket chamber.
机译：先进且密集的计算解决方案开发与渐近技术相集成，以检查燃烧表面形态对固体航天器内具有宽范围强迫频率的旋转流场的影响。模拟的矩形腔室的一端是封闭的，而后端是开放的。上壁和下壁是可渗透的，以允许稳定和不稳定的注入空气产生内部流，从而模拟真实火箭室内燃烧气体的流场。不稳定注入流的频率选择为非常接近或远离适配腔室的共振频率。当前的研究说明了反映真实燃烧过程复杂性的大范围波数。本研究介绍了在腔室四个边界处的Navier-Stokes方程的详细推导。定性比较是使用聚乙烯和铝粉的混合物在两英寸混合动力火箭发动机上进行的最新实验工作进行的。混合物中铝粉的百分比越高，燃烧表面的波纹越多。这种趋势几乎类似于模拟的固体火箭舱的计算和分析结果。

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  • 来源
    《Mathematical Problems in Engineering》 |2015年第1期|485302.1-485302.11|共11页
  • 作者

    Hegab Abdelkarim M.; Sait Hani Hussain; Hussain Ahmad;

  • 作者单位

    King Abdulaziz Univ, Fac Engn, Dept Mech Engn, Rabigh 21911, Saudi Arabia.;

    King Abdulaziz Univ, Fac Engn, Dept Mech Engn, Rabigh 21911, Saudi Arabia.;

    King Abdulaziz Univ, Dept Nucl Engn, Jeddah 21589, Saudi Arabia.;

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