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[1]孙 迪,马 亮,甘晓松,等.嵌金属丝两级药柱掺混燃烧下的内弹道计算[J].火箭推进,2019,45(03):59-63.
　SUN Di,MA Liang,GAN Xiaosong,et al.Internal ballistics calculation under mixing combustion of two-stage grain with embedded wire[J].Journal of Rocket Propulsion,2019,45(03):59-63.
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嵌金属丝两级药柱掺混燃烧下的内弹道计算

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 45 期数: 2019年03期 页码: 59-63 栏目: 研究与设计 出版日期: 2019-06-30
Title:
Internal ballistics calculation under mixing combustion of two-stage grain with embedded wire
文章编号:
1672-9374(2019)03-0059-05
作者:
孙 迪; 马 亮; 甘晓松; 郭运强
(西安航天动力技术研究所, 陕西 西安 710025)
Author(s):
SUN Di;  MA Liang;  GAN Xiaosong;  GUO Yunqiang
(Xi'an Institute of Aerospace Propulsion Technology, Xi'an 710025, China)
关键词:
固体火箭发动机;  嵌金属丝;  单室双推力;  掺混燃烧;  内弹道
Keywords:
solid rocket motor;  embedded wire;  single-chamber dual-thrust;  mixing combustion;  internal ballistics
分类号:
V435
文献标志码:
A
摘要:
为了预示嵌金属丝端燃药柱和后翼柱药柱掺混燃烧条件下单室双推力发动机的内弹道性能,首先对高压段和低压段燃烧过程中的复杂燃面变化进行分析,获得不同增速比对应的燃面与基准燃面之间的关系。然后,考虑压强转级对增速比的影响,获得过渡段二者的关系,从而实现了整个燃烧过程增速比的无级变速,进而获得燃面退移规律,据此计算了这种类型装药发动机的内弹道性能。结果表明:计算值与试验曲线吻合良好,计算误差小于5%,证明了计算模型的合理性和程序的可靠性。该方法可用于此类型发动机的内弹道计算与分析。
Abstract:
In order to predict the internal ballistics performance of a single-chamber dual-thrust motor under the mixing combustion condition of end-burning grain with embedded wire and rear wing grain, the changes of complex combustion surface during the combustion process of the high pressure stage and the low pressure stage were first analyzed.The relationship between the combustion surface and the reference combustion surface corresponding to different speed increasing ratio was obtained.Then, considering the effect of pressure transfer on the speed increasing ratio, the relationship between them in the transition stage was obtained.Thereby, its stepless variable speed during the entire combustion process was realized, and the law of burning surface regression was obtained.Accordingly, the internal ballistic performance of this type of motor was calculated.The results show that the calculated values agree well with the experimental curves, and the calculation error is less than 5%, which proves the rationality of the calculation model and the reliability of the program.The method can be used for the internal ballistic calculation and analysis of this type of motor.

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备注/Memo

收稿日期:2018-01-14
基金项目:国家自然科学基金(11702205)
作者简介:孙 迪(1989—),女,硕士,工程师,研究领域为固体火箭发动机设计

更新日期/Last Update: 2019-06-30