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Study of Maximum Pressure Rise with Erosive Burning in Multi‐Grain Tubular Solid Propellant
Propellants, Explosives, Pyrotechnics ( IF 1.8 ) Pub Date : 2020-07-16 , DOI: 10.1002/prep.202000063
Balesh Ropia 1 , Jayesh Upadhyay 1 , Rakesh Kalal 1 , Himanshu Shekhar 2 , Dinesh G. Thakur 3
Affiliation  

In the present study, the mathematical prediction with the Paul‐Mukunda model is carried out for maximum pressure rise with erosive burning in multi‐grain solid rocket propellant. For this study, a cluster of 7 tubular solid double‐base propellant grains is selected. The erosive burning model has given a fair idea of the maximum pressure rise in rocket motors. The maximum pressure rise due to the erosive burning effect is quite a lot higher than without the erosive burning effect. The erosive burning model helps in studying maximum pressure rise for various configurations of propellant grains. It is found that lowering the outer diameter (OD) of propellant grains is giving low maximum pressure in rocket motor in comparison to increasing the inner diameter (ID) of propellant grains. Ap/At (port area to throat area) ratio is maintained same for both the cases. Although in both the cases predicted maximum flow velocity of propellant gases is almost same. It shows that keeping the same Ap/At ratio and erosive burning effect, the maximum pressure is reduced significantly by lowering OD of propellant grains than increasing the ID of the propellant grains in rocket motor. This study will help to reduce the maximum pressure rise in rocket motors for safe working.

中文翻译:

多颗粒管状固体推进剂侵蚀燃烧最大压力上升的研究

在本研究中,使用Paul-Mukunda模型进行了数学预测,以在多颗粒固体火箭推进剂中通过侵蚀性燃烧最大压力升高。对于本研究,选择了由7个管状双基固体推进剂颗粒组成的簇。侵蚀燃烧模型对火箭发动机的最大压力上升给出了一个合理的想法。与没有侵蚀燃烧作用的情况相比,由于侵蚀燃烧作用的最大压力升高要高得多。侵蚀燃烧模型有助于研究推进剂颗粒各种构造的最大压力升高。已经发现,与增加推进剂颗粒的内径(ID)相比,降低推进剂颗粒的外径(OD)在火箭发动机中产生的最大压力较低。甲p / A两种情况下的(端口面积与喉部面积)比保持相同。尽管在两种情况下预测的推进剂气体的最大流速几乎相同。结果表明,在保持相同的A p / A t比和侵蚀燃烧效果的情况下,通过降低推进剂颗粒的OD比增加火箭发动机中推进剂颗粒的ID可以显着降低最大压力。这项研究将有助于减少火箭发动机的最大压力上升,以确保安全工作。
更新日期:2020-09-02
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