侧向收缩比对RBCC侧压式进气道起动性能的影响  

The Influence of Sidewall Contraction Ratio on the Starting Performance of RBCC Supersonic Sidewall-compression Inlet

作　　者：吴亚可[1] 何国强[1] 刘佩进[1] 刘晓伟[1] 

机构地区：[1]西北工业大学固体火箭发动机燃烧热结构与内流场国防科技重点实验室,西安710072

出　　处：《弹箭与制导学报》2011年第3期146-150,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：低来流马赫数时,侧向压缩将是RBCC发动机进气道的主要压缩形式。文中开展了侧向收缩比对RBCC侧压式进气道起动性能的影响研究。采用数值模拟方法获得了进气道的流场分布和性能参数。结果发现,不同侧向收缩比的进气道在起动过程中都伴随着流场结构的突变,且该突变和总压恢复系数的突然增加是同步的,这种同步性对应的来流马赫数就是进气道的起动马赫数。对于RBCC侧压式进气道,需权衡利弊,选取大小合适的侧向收缩比。Sidewall compression is the primary compression form for rocket based combined cycle （RBCC） engine during low operating Mach numbers. It was investigated in this paper that the influence of sidewall contraction ratio on the starting performance of a typical RBCC supersonic sidewall-compression inlet. Performance parameters and flow field characters were attained by numerical simulation. The investigation shows that mutation of the flow field occurs during the starting process for the inlet with different sidewall contraction ratio. This mutation is synchronous with the sudden augment of the total pressure recovery. The Mach num bet corresponding with this synchronicity is the starting Mach number. It is advisable to choose RBCC inlet with moderate sidewall contracnon ratio.

关 键 词：RBCC发动机 侧压式进气道 进气道起动 侧向收缩比 数值模拟 

分 类 号：V233.6[航空宇航科学与技术—航空宇航推进理论与工程]