固体火箭超燃冲压发动机硼基贫氧推进剂配方优选试验研究  

Experimental study on the selection of boron-based propellant for solid-fuel rocket scramjet

作　　者：黄礼铿 魏和平 张先瑞[2] 杨玉新 田凌寒 张强 HUANG Likeng;WEI Heping;ZHANG Xianrui;YANG Yuxin;TIAN Linghan;ZHANG Qiang(The 41st Institute of the Fourth Academy of CASC,Xi'an 710025,China;Hubei Institute of Aerospace Chemotechnology,Xiangyang 441003,China)

机构地区：[1]中国航天科技集团有限公司四院四十一所,西安710025 [2]湖北航天化学技术研究所,襄阳441003

出　　处：《固体火箭技术》2022年第1期97-102,共6页Journal of Solid Rocket Technology

摘　　要：针对固体火箭超燃冲压发动机中高焓多相超音速燃烧组织难题,通过改进含硼固体贫氧推进剂配方,为硼颗粒的点火燃烧提供良好的微环境,以进一步缩短硼颗粒的点火延迟时间,开展了三种推进剂配方的直连试验研究。试验结果表明,在5~10μm粒径的基础上,进一步降低硼颗粒粒径至1~2μm,使颗粒的随流性增强,并使得掺混均匀度降低,抵消了硼颗粒粒径减小带来的燃烧性能优化作用;提高一次燃烧效率,使得一次燃气温度提升,硼颗粒的点火燃烧微环境得到改善,显著提高了一次燃气的超音速补燃效率。在试验工况下,硼颗粒的燃烧效率由基础配方的61.2%提高至83%,计算得到的发动机名义比冲由6016 N·s/kg提高至7996 N·s/kg,使其超音速燃烧性能得到了显著提高。Based on the problem of multiphase supersonic combustion in solid-fuel rocket scramjet,an improved combustion environment was provided for boron particles by optimizing the formulation of boron-based solid propellant,aiming to further shorten the ignition delay time of boron particles.Direct connection tests of three propellant formulations were carried out.The results show that reducing boron particle size from 5~10μm to 1~2μm,the fluidity of boron particles is enhanced,but the mixing uniformity is reduced,leading to an offsetting effect on the combustion performance.On the other side,the improved primary combustion efficiency increases the primary gas temperature,and improves the microenvironment of ignition and combustion for boron particles.Therefore,the efficiency of supersonic combustion of primary gas is significantly improved.Under the test conditions,the combustion efficiency is improved from 61.2%to 83.0%,and the calculated nominal specific impulse increases from 6016 N·s/kg to 7996 N·s/kg.

关 键 词：固体火箭超燃冲压发动机 直连试验 含硼固体贫氧推进剂 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]