火箭推进2024，Vol.50Issue(3)：90-101,12.DOI:10.3969/j.issn.1672-9374.2024.03.010
固体火箭发动机中最终凝相产物特性分析
Characteristics of final condensate products in solid rocket engine
摘要
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(stages①～③)according to the pressure distribution in the combustion chamber.In stage①,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 stage②,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.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Key words
solid rocket motor/aluminized composite propellant/condensate products/particle size distribution/dynamic particle size measurement分类
航空航天引用本文复制引用
刘梦莹,徐晨恩,黄河峡,蔡佳,刘筑,李世鹏..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(3):90-101,12.基金项目
国家自然科学基金(22205107) （22205107）
江苏省卓越博士后计划(2022BZ212) （2022BZ212）
进排气技术教育部重点实验室基金(CEPE2020012) （CEPE2020012）
