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固体火箭冲压发动机含硼推进剂燃烧性能实验研究
引用本文:赵瑞杰,张淋清,蔡文祥,任建德,王禄浩,陈雄.固体火箭冲压发动机含硼推进剂燃烧性能实验研究[J].推进技术,2022,43(9):413-424.
作者姓名:赵瑞杰  张淋清  蔡文祥  任建德  王禄浩  陈雄
作者单位:1.南京理工大学 机械工程学院,江苏 南京 210094;2.内蒙动力机械研究所,内蒙古 呼和浩特 010031;3.哈尔滨工业大学 能源科学与工程学院,黑龙江 哈尔滨 150001
基金项目:国家自然科学基金(51306092)。
摘    要:利用地面直连试验系统对含硼推进剂在某固体火箭冲压发动燃烧过程性能进行试验研究。通过对含硼推进剂燃烧后凝聚相样品的SEM,EDS和XPS分析,探讨推进剂燃烧过程。在凝聚相EDS分析中,硼元素含量随着远离推进剂轴向方向显著降低,氧元素含量显著升高。在补燃室中,由于补充富氧空气,一次燃烧产物进一步反应,导致环境温度上升。由于高温,硼颗粒发生燃烧,产生大量气态硼化物,从而导致硼元素含量下降。二次燃烧凝聚相产物中,硼的非完全氧化物占比在40%以上,氮化硼占比在20%以上,硼颗粒占比7%以下。研究结果表明,随着推进剂在燃气发生器和补燃室内的一、二次燃烧,硼颗粒逐渐减少,并分别与环境中的C和O等元素发生化学反应,在凝聚相中的含量逐渐降低,氧元素在补燃室之后显著增加,氮化硼为凝聚相主要成分之一,存在于各特征位置。推进剂中的硼颗粒没有被完全燃烧,燃烧效率有待于进一步提高。

关 键 词:固体火箭冲压发动机  含硼推进剂  凝聚相产物  取样方法  产物分析
收稿时间:2021/6/11 0:00:00
修稿时间:2021/8/10 0:00:00

Experimental Study on Combustion Performance of Propellant Containing Boron for Solid Rocket Ramjet
ZHAO Rui-jie,ZHANG Lin-qing,CAI Wen-xiang,REN Jian-de,WANG Lu-hao,CHEN Xiong.Experimental Study on Combustion Performance of Propellant Containing Boron for Solid Rocket Ramjet[J].Journal of Propulsion Technology,2022,43(9):413-424.
Authors:ZHAO Rui-jie  ZHANG Lin-qing  CAI Wen-xiang  REN Jian-de  WANG Lu-hao  CHEN Xiong
Institution:1.School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China;2.Inner Mongolia Power Machinery Research Institute,Hohhot 010031,China;3.School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,China
Abstract:The combustion performance of boron propellant in a solid rocket was studied by ground direct connection test system. The combustion process of the boron-containing propellant was investigated by SEM, EDS and XPS analysis of the condensed phase samples after combustion. In the EDS analysis of condensed phase, the content of boron decreases significantly along the axial direction away from the propellant, and the content of oxygen increases significantly. Boron particles combustion occurs as the ambient temperature rises during the secondary combustion process. The reaction produces a large amount of gaseous borides, resulting in a decrease in boron content. In the condensed phase products of secondary combustion, the mass proportion of incomplete oxides of boron is more than 40%; the mass proportion of boron nitride is more than 20%; and the mass proportion of boron particles is less than 7%. The results show that with the primary and secondary combustion of the propellant in the gas generator and the supplementary combustion chamber, the boron particles decrease gradually and react with the elements such as C and O in the environment respectively. The content of boron particles in condensed phase decreases gradually and the content of oxygen element increases significantly in the back of the combustion chamber. As one of the main components of condensed phase, boron nitride exists in various characteristic locations. The boron particles in the propellant have not been completely burned and the combustion efficiency needs to be further improved.
Keywords:Solid rocket ramjet  Boron-based propellant  Condensed combustion products  Sampling method  Product analysis
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