宇航学报 ›› 2019, Vol. 40 ›› Issue (10): 1157-1166.doi: 10.3873/j.issn.1000-1328.2019.10.006

• 综述 • 上一篇    下一篇

固体发动机燃烧流动基础问题与研究建议

吕翔,何国强,刘佩进,李强   

  1. 西北工业大学燃烧、热结构与内流场重点实验室,西安 710072
  • 收稿日期:2019-06-15 修回日期:2019-07-13 出版日期:2019-10-15 发布日期:2019-10-25

Requests and Suggests for Basic Research on SRM Combustion and Flow

LV Xiang, HE Guo qiang, LIU Pei jin, LI Qiang   

  1. National Key Laboratory of Combustion, Thermal Structure and Flow, Northwestern Polytechnical University, Xi’an 710072, China
  • Received:2019-06-15 Revised:2019-07-13 Online:2019-10-15 Published:2019-10-25

摘要:

针对固体火箭发动机(SRM)的未来发展进行了探讨,提出了多学科协同的发动机总体设计优化技术、发动机精细化设计和性能精确调控技术、发动机虚拟试验与数字孪生技术以及发动机先进试验与测量技术是支撑固体发动机未来发展和应用的重要技术。为了实现固体发动机的细粒度建模、多维度设计和高精度仿真,在燃烧流动领域需要重点关注的基础问题包括:发动机环境下固体推进剂细观燃烧机理和燃烧模型、发动机内凝相运动行为模式及多相流输运规律、发动机非线性燃烧不稳定机理、凝相撞击壁面的行为模式和对壁面的力热作用规律、多相燃烧产物作用下绝热结构失效模式与破坏机理、多相燃烧产物生成与输运过程对能量转换的影响机理。最后提出了相关建议,以期更好地推动固体发动机燃烧流动领域的基础研究,更好地服务于固体发动机技术的未来发展。

关键词: 固体火箭发动机, 固体推进剂, 燃烧不稳定, 多相流, 烧蚀, 热力计算

Abstract:

In this paper, the development trend of solid rocket motor (SRM) is discussed, and it is considered that high energy, high pressure, high overload, wide adaptation and extreme dimension are the most important development trends. The most important supporting techniques for the future development and applications of SRM include multi-discipline design and optimization, refinement design and performance precision control, virtual test and digital twin, and advanced experiment and measurement technology. In order to achieve the fine-grained modeling, multi-dimension design and high-precision simulation of SRM, the basic issues of combustion and flow in SRM that need to be paid attention to include combustion mechanism and model of solid propellant on mesoscopic scale, condensed phase motion behavior and multiphase flow transportation law, nonlinear combustion instability mechanism, impact pattern and force/heat effect of condensed phase on the wall surface, ablation mechanism and failure mode of adiabatic structure, energy release and conversion law during the formation and transportation procedure of a multiphase combustion product. At the end of the paper, the suggestions are proposed for better achievement in the forementioned basic research, and better development of SRM.

Key words:  Solid rocket motor, Solid propellant, Combustion instability, Multiphase flow, Ablation, Thermodynamics calculation

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