H_2O_2/HTPB固液混合发动机点火试验研究  

Experimental Investigation on Ignition of H_2O_2/HTPB Hybrid Rocket Engine

作　　者：宋志兵[1] 王振国[1] 张炜[1] 夏智勋[1] 胡建新[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2008年第1期28-31,共4页Journal of National University of Defense Technology

基　　金：国家863基金资助项目(2007AA702312)

摘　　要：利用H2O2催化分解原理,设计了烃类燃料在催化分解的90%H2O2中能燃烧的点火器,然后采用该点火器进行H2O2/HTPB固液混合发动机点火试验研究。试验结果表明,该点火器能够成功启动H2O2/HTPB固液混合发动机,且当混合比偏离最佳混合比后,发动机的燃烧效率降低。An innovative igniter based on catalytic decomposition of H2O2 was designed and manufcatured. With this igniter, an HeO2/HTPB hybrid rocket engine was tested. The experiment results demonstrate that this new igniter can successfully start the H2O2/ HTPB hybrid rocket engine with combustion stability and good performance. The experiment results also show that the combustion efficiency will achieve the highest level when the hybrid ratio deviates from the best ratio of oxidizer.

关 键 词：固液混合发动机 燃烧过程 点火试验 固液混合推进剂 

分 类 号：V436[航空宇航科学与技术—航空宇航推进理论与工程]