Impact Analysis of Combustion Exhaust Coriolis Acceleration in Solid Rocket Motor

被引：0
|
作者：
Wang L.-W. [1 ]
Tian W.-P. [1 ,2 ]
Guo Y.-Q. [3 ]
Lin Z.-Y. [1 ]
机构：
[1] National Key Laboratory of Combustion, Flow and Thermo-Structure, Northwestern Polytechnical University, Xi'an
[2] Research Institute of Aerospace Propulsion, Xi'an
[3] Xi'an Institute of Aerospace Propulsion, Xi'an
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2019年 / 40卷 / 03期
关键词：
Coriolis acceleration; Impact; Overload; Solid rocket motor;
D O I：
10.13675/j.cnki.tjjs.180269
中图分类号：
学科分类号：
摘要：
In order to reveal the cause of lateral overload for solid rocket motor(SRM) and analyze influence factors of Coriolis acceleration for combustion exhaust, a method of theoretical analysis and experimental verification is used. The results show that SRM lateral acceleration is a comprehensive effect of Coriolis acceleration and normal implicated one, Coriolis acceleration has an inverse relationship with turning radius of missile and direct linear relationship with missile velocity and combustion exhaust velocity. Simulation rotating overload tests on the ground show that lateral acceleration cause alumina particle aggregation toward SRM surface, which will result in much more serious ablation in this region than others. In addition, Coriolis acceleration will lead to a phenomenon that the direction of real lateral overload is not the direction created by implicated acceleration. Consequently, the direction with much more serious nozzle ablation has a circular angle with implicated acceleration. © 2019, Editorial Department of Journal of Propulsion Technology. All right reserved.
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页码：481 / 486
页数：5
相关论文
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