Universal erosive burning model performance for solid rocket motor internal ballistics
Universal erosive burning model performance for solid rocket motor internal ballistics
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DOI：
10.1016/j.ast.2015.05.005
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发表时间：
2015-09
影响因子：
5.6
通讯作者：
Afroz Javed;D. Chakraborty
中科院分区：
文献类型：
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作者：
Afroz Javed;D. Chakraborty
固体火箭推进剂的烧蚀燃烧是L/D型高性能火箭发动机所关注的问题。对这一现象的不同原因有几种解释，并有根据这些原因预测影响的建模做法。Mukunda和Paul提出了侵蚀性燃烧过程的普遍性质，而不考虑推进剂的大小、形状和类型。在本工作中，同样的模型也适用于高和中等质量通量的圆柱形端口电机，以及翅片颗粒电机。结果表明，对于圆柱形端口发动机，计算压力与燃烧时间的关系与实验数据吻合得很好。将修正后的模型(即原来的轴对称流道模型)用于流道几何形状，得到了较好的压力预测结果。这项研究证实了Mukunda和Paul模型在其修改形式中的普适性，该模型也处理非轴对称端口几何形状。该模型的简单性使其成为设计和分析任何尺寸和流道几何形状的固体火箭发动机的有用工具。
The erosive burning of solid rocket propellant is an area of concern for high L/D rocket motors. Several explanations for the different causes for this phenomenon exist along with the modelling practices to predict the effects based on these causes. Universal nature of the erosive burning process was proposed by Mukunda and Paul irrespective of size, shape and type of the propellant. In the present work, the same model is applied for cylindrical port motors with high and moderate mass flux, as well as finocyl grain motors. It is observed that for cylindrical port motors, computed pressures with the burning time match very well experimental data. A modified form of the model (which becomes the original model for axisymmetric port) is used for finocyl geometries and a good prediction of pressures is observed. This study confirms the universality of the Mukunda and Paul model in its modified form which addresses non-axisymmetric port geometries also. The simplicity of the model makes it a useful tool for design and analysis of solid rocket motors of any size and port geometry.