固冲发动机补燃室二次燃烧实验研究  

Experimental investigation on secondary combustion in solid rocket ramjet

作　　者：李纲[1] 何国强[1] 孙振华[2] 曹军伟[2] 王虎干[2] 

机构地区：[1]西北工业大学航天学院,西安710072 [2]中国空空导弹研究院,洛阳471009

出　　处：《固体火箭技术》2007年第5期400-403,共4页Journal of Solid Rocket Technology

摘　　要：采用不确定度评定的地面直连冲压实验设备,对某全尺寸固冲发动机补燃室二次燃烧进行了实验研究。通过测定比冲效率,确定了不同的燃气发生器喷嘴结构、空气进气角度、进气头部距离和补燃室长度对二次燃烧的影响,并进行了机理分析。结果表明,五喷嘴比冲效率较高,燃气的切入方式对补燃室二次燃烧有重要影响;增大入射角度,可提高比冲效率,但加剧了燃烧产物在补燃室内的沉积;补燃室头部距离不宜过大,比冲效率不随头部距离线性增加;补燃室长度增加,可使比冲效率提高,但效果并不理想。The secondary combustion of full-scale solid rocket ramjet was investigated by using the ground direct-connected experimental equipment with uncertainty evaluation. The effects of injector configuration of different gas generator,air inlet angle,dome height and length of secondary chamber on secondary combustion were determined by measuring the impulse efficiency, and their effect mechanism was analyzed. The analysis results show that the impulse efficiency of solid rocket ramjet with five injectors is higher;the inlet way of gas has an important effect on the secondary combustion in secondary chamber;the increase of inlet angle can effectively improve impulse efficiency, but intensify the deposition of combustion product in the secondary chamber; the dome height of secondary chamber should not be too big;the impulse efficiency cannot linearly increase with the dome height;the increase of secondary chamber length can improve the impulse efficiency, but the effectiveness isnt satisfactory.

关 键 词：固体火箭冲压发动机 含硼富燃料推进剂 二次燃烧 机理分析 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]