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[1]刘梦莹,徐晨恩,黄河峡,等.固体火箭发动机中最终凝相产物特性分析[J].火箭推进,2024,50(03):90-101.[doi:10.3969/j.issn.1672-9374.2024.03.010]
　LIU Mengying,XU Chen'en,HUANG Hexia,et al.Characteristics of final condensate products in solid rocket engine[J].Journal of Rocket Propulsion,2024,50(03):90-101.[doi:10.3969/j.issn.1672-9374.2024.03.010]
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固体火箭发动机中最终凝相产物特性分析

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 50 期数: 2024年03期 页码: 90-101 栏目: 目次 出版日期: 2024-06-25
Title:
Characteristics of final condensate products in solid rocket engine
文章编号:
1672-9374(2024)03-0090-12
作者:
刘梦莹1; 徐晨恩1; 黄河峡1; 蔡佳1; 2; 刘筑3; 李世鹏4
1.南京航空航天大学 能源与动力学院,江苏 南京 210016; 2.南京工业职业技术大学 航空工程学院,江苏 南京 210023; 3.空间物理重点实验室,北京 100076; 4. 北京理工大学 宇航学院,北京 100086
Author(s):
LIU Mengying1;  XU Chen'en1;  HUANG Hexia1;  CAI Jia1; 2;  LIU Zhu3;  LI Shipeng4
1.College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China; 2.College of Aviation Engineering, Nanjing Vocational University of Industry Technology, Nanjing 210023, China; 3.Science and Technology on Space Physics Laboratory, Beijing 100076, China; 4.School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100086, China
关键词:
固体火箭发动机;  含铝复合推进剂;  凝相产物;  粒径分布;  动态粒径测量
Keywords:
solid rocket motor;  aluminized composite propellant;  condensate products;  particle size distribution;  dynamic particle size measurement
分类号:
V512
DOI:
10.3969/j.issn.1672-9374.2024.03.010
文献标志码:
A
摘要:
铝颗粒的加入可以有效提高固体推进剂的能量特性,但也带来了两相流比冲损失、熔渣沉积和喷管烧蚀加剧等消极影响,因此,对固体火箭发动机最终凝相产物特性展开研究对评估和提升固体火箭发动机性能具有重要意义。以燃烧终产物为主要研究对象,搭建了基于粒度分析仪的高温高速颗粒特性动态测量系统,对AP/HTPB含铝复合推进剂开展了高温高压下固体火箭发动机试验研究,获得了排气羽流中燃烧终产物分布特性,包括燃烧终产物粒径、均值粒径及颗粒种类等随时间的变化规律,为全面了解凝相产物粒度分布特性提供试验和数据支撑。根据发动机燃烧室压力分布趋势,将固体火箭发动机的工作过程划分为3个阶段(阶段①～③),研究表明:阶段①排气羽流中固体颗粒包括黑火药和推进剂两种燃烧产物,黑火药的随机燃烧特性、燃烧室压力和温度的突升会共同影响该阶段的燃烧终产物分布特性; 阶段②燃烧稳定性最高,且该阶段不同时刻燃烧终产物粒径具有较为一致的分布特性,可采用特征模式描述阶段②燃烧终产物的粒径分布; 阶段③燃烧终产物粒径分布离散度小于阶段①,该阶段燃烧室压力和温度的突降会影响燃烧终产物分布特性; 燃烧室压力和温度突变会改变燃烧终产物模态、峰值粒径及均值粒径等分布特性,不同类型颗粒质量分数随发动机工作阶段的变化而变化。
Abstract:
The addition of aluminium particles can effectively improve the energy characteristics of solid propellants, but it also brings negative effects such as specific impulse loss, slag deposition, and intensified nozzle erosion. Therefore, conducting research on the characteristics of final condensed phase products in solid rocket motors is of great significance for evaluating and improving the performance of solid rocket engines. The final condensate products were taken as the main research object, and a dynamic measurement system for high-temperature and high-speed particle characteristics based on particle size analyser was built for experimental research on AP/HTPB aluminized composite propellant under the real working condition of solid rocket engine. The distribution characteristics of final condensate products in the exhaust plume, including the change laws of the particle size, average particle size and types of final condensate products were revealed in this paper. It provides experimental and data support for comprehensively understanding the size distribution characteristics of condensed products. The working process of solid rocket engine can be divided into three stages(stages ①～③)according to the pressure distribution in the combustion chamber. In stage ①, The research shows that the condensate products in the exhaust plume include the combustion products of powder explosive and propellant. The random combustion characteristics of powder explosive and the sudden rise of pressure in the combustion chamber will jointly affect the distribution characteristics of condensate products at this stage. The size distribution of condensate products has the highest stability in stage ②, and characteristic distribution can be applied to describe the size distribution of condensate products. The dispersion of size distribution of condensate products in stage ③ is smaller than that in stage ①, and a sudden drop of pressure in combustion chamber during this stage will affect the distribution characteristics of condensate products. Sudden changes in combustion chamber pressure and temperature can alter the distribution characteristics of condensate products modes, peak particle size, and mean particle size. Meanwhile, the mass fraction of different types of condensate products varies with the operating stage of the solid rocket engine.

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备注/Memo

收稿日期:2023- 11- 25修回日期:2024- 01- 17
基金项目:国家自然科学基金(22205107); 江苏省卓越博士后计划(2022BZ212); 进排气技术教育部重点实验室基金(CEPE2020012)
作者简介:刘梦莹(1994—),女,博士,讲师,研究领域为金属颗粒掺混燃烧特性。
通信作者:黄河峡(1989—),男,博士,副教授,研究领域为内流空气动力学。

更新日期/Last Update: 1900-01-01