多分支管脉冲爆震火箭发动机的实验研究  

Experimental Investigation on Multi-splitted Tubes Pulse Detonation Rocket Engine

作　　者：秦红强[1] 范玮[1] 李建玲[1] 严宇[1] 

机构地区：[1]西北工业大学动力与能源学院

出　　处：《弹箭与制导学报》2010年第4期113-116,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家自然科学基金(50976094);教育部新世纪优秀人才计划(NCET-04-0960)资助

摘　　要：为了探索新的脉冲爆震火箭发动机（PDRE）构型，以单管构型为基准，实验研究了爆震波从单管向双分支管、三分支管和四分支管传播的情况。结果表明分支管内也可形成爆震波，但是随着分支管数目的增加，爆震波衰减越明显。新的PDRE构型也会影响发动机的推力性能，其中双分支管PDRE和三分支管PDRE的推力性能得到了改善，分别比单管PDRE提高了73．28％和18．38％．四分支管PDRE的推力则由于爆震波过度衰减而降低了4．89％。To explore new pulse detonation rocket engine （PDRE） structure, an experimental investigation on the propagations of the detonation wave from single tube to dual-spiRted tube, three-splitted tube and four-splitted tube configurations are investigated using the single tube configuration as a baseline case. The results indicate that detonation wave can form in the splitted tubes, hut with the increase of the number of spliited tubes, the detonation wave decays more. What＇s more, the thrust performance of new PDRE structures is also influenced. Compared with single tube, the thrust of dual-splitted tube and three-splitted tube are improved by 73.28% and 18.38 % respectively while the thrust of the four-spiRted tube is decreased by 4.89 % as a result of detonation wave deterioration.

关 键 词：脉冲爆震火箭发动机 分支管 推力 

分 类 号：V231.22[航空宇航科学与技术—航空宇航推进理论与工程]