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兵工学报 ›› 2021, Vol. 42 ›› Issue (9): 1877-1887.doi: 10.3969/j.issn.1000-1093.2021.09.008

• 论文 • 上一篇    下一篇

横向过载对固体火箭发动机推进剂点火建压过程的影响

官典1, 李世鹏1, 刘筑2, 王宁飞1   

  1. (1.北京理工大学 宇航学院, 北京 100081; 2.中国运载火箭技术研究院 空间物理重点实验室, 北京 100076)
  • 上线日期:2021-10-20
  • 作者简介:官典(1992—),男,博士研究生。E-mail:805233853@qq.com
  • 基金资助:
    军队科研项目(2019年)

Influence of Lateral Acceleration on Ignition Transients of Solid Rocket Motor

GUAN Dian1, LI Shipeng1, LIU Zhu2, WANG Ningfei1   

  1. (1.School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;2.Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing 100076, China)
  • Online:2021-10-20

摘要: 大过载下固体火箭燃烧与流动状态的剧烈变化会导致内弹道出现异常,严重时可能会引起发动机点火失败。为研究横向过载时点火内弹道特性,建立囊括流场惯性过载效应、过载燃烧效应和侵蚀燃烧效应的点火模型。对不同横向过载下燃烧室压力和侵蚀与过载效应燃速增速占比进行计算,并给出了推进剂火焰传播速度与升压速率的关系。结果表明:正向过载下压力峰值增加,负向过载下压力峰值降低;正向过载下,推进剂前段主要由过载效应影响,后段主要由侵蚀效应影响;正向过载加剧下游侵蚀效应,而负向过载对推进剂的燃烧起削弱作用,但程度较弱、持续时间较短;火焰传播速度峰值时刻、推进剂表面首次全部点燃时刻和升压速率峰值点时刻几乎一致,工程上可以用实验中获得的升压速率分析推进剂表面燃烧状况。

关键词: 固体火箭发动机, 推进剂, 横向过载, 点火建压, 数值计算

Abstract: The high acceleration is found to alter the internal ballistic performance and induce ignition abnormalities by changing the internal flow and combustion state in the rocket chamber.To demonstrate the mechanism of interior ballistics as the results of acceleration loads imposed, the modes of the acceleration field effect, acceleration combustion effect, and erosion combustion characteristics are developed and first taken into in a new ignition model.The transient pressure in combustion chamber and the proportion of erosion and acceleration effects versus time are obtained. The relationship between propellant flame propagation speed and pressure rise rate is proposed. The results show that the peak-pressure is increased under the condition of positive acceleration and weakened under the condition of negative acceleration. Under the condition of positive acceleration, the front section of propellant is mainly affected by the acceleration-combustion, and the rear section is mainly affected by the erosion-combustion. By intensifying upstream combustion,the downstream erosion effect is aggravated by the positive acceleration. The negative acceleration is found with a less weakening effect on the combustion of propellant in the rocket, both in magnitude and time duration.The moment of peak of flame-spread velocity is almost identical to the moment of ignition of the entire propellant grain and the peak of pressure-rate.Therefore, the pressure-rise rate of the pressure data obtained in the experiment can be suggested to analyze the surface combustion of propellant.

Key words: solidrocketmotor, propellant, lateralacceleration, ignitioninterval, numericalsimulation

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