固体火箭技术2017，Vol.40Issue(3)：277-282,294,7.DOI:10.7673/j.issn.1006⁃2793.2017.03.002
基于DMSJ发动机流道的RBCC发动机设计
RBCC engine design based on the flow passge of DMSJ engine
刘晓伟 1石磊 1刘佩进 1秦飞 1何国强 1赵建辉2
作者信息
- 1. 西北工业大学 航天学院,西安 710072
- 2. 空军西安飞行学院,西安 710306
- 折叠
摘要
Abstract
The flow passage and combustion organization design of a DMSJ engine is carried out firstly.The specific impulse of the DSMJ engine is 1029.6 s when M∞=4.0,whereas it is 899.9 s when M∞=6.0.A RBCC engine flow passage is obtained by pla-cing a rocket engine on the isolation sidewall of the DMSJ engine.Investigation shows that the rocket shoulder and downstream flow passage scheme variation have limited influence on engine specific impulse when M∞ is lower.The RBCC engine specific impulse is 1052.8s when M∞=4.0,with the same fuel injection mode as the DMSJ engine.In order to gain a comparable specific impulse to that of DMSJ engine when M∞ is higher,the fuel injection mode of the RBCC engine should be different from the DMSJ engine.The com-bustion organization positions of two engines are both in the upstream flow passage when M∞ is elevated.The specific impulse of RB-CC engine is 887.8 s when M∞=6.0,with the regulating of the fuel injection mode.Therefore,it is facile and feasible to design a RBCC engine based on traditional mature DMSJ engine.关键词
双模态冲压发动机/火箭基组合循环发动机/燃烧组织/比冲/数值模拟Key words
DMSJ engine/RBCC engine/combustion organization/specific impulse/numerical simulation分类
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刘晓伟,石磊,刘佩进,秦飞,何国强,赵建辉..基于DMSJ发动机流道的RBCC发动机设计[J].固体火箭技术,2017,40(3):277-282,294,7.
