Experimental and Numerical Investigation of a Solid-Fuel Rocket Scramjet Combustor
Experimental and Numerical Investigation of a Solid-Fuel Rocket Scramjet Combustor
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DOI：
10.2514/1.b35838
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发表时间：
2016-03
影响因子：
1.9
通讯作者：
Zhong Lv;Z. Xia;Bing Liu;Yuanchun Liu
中科院分区：
文献类型：
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作者：
Zhong Lv;Z. Xia;Bing Liu;Yuanchun Liu
提出了一种以固体燃料为推进剂的新型超燃冲压发动机构型，即固体燃料火箭超燃冲压发动机。对固体燃料火箭发动机超燃冲压发动机燃烧室进行了实验和数值模拟研究。该实验模拟了17公里高空4马赫的飞行环境。镁基固体燃料作为推进剂在这项研究中使用。结果表明，超声速燃烧室中存在二次燃烧现象。推进剂的燃烧效率约为65%，总压恢复约为0.5。这表明采用固体燃料作为推进剂的超燃冲压发动机构型是可行的。数值分析的结果表明，在燃烧室的核心流中产生了一个正激波，这是由于所有的富燃料气体被注入在同一个横截面。
A new scramjet configuration using solid fuel as propellant is proposed, namely, the solid-fuel rocket scramjet. Experimental and numerical investigation of the solid-fuel rocket scramjet combustor was conducted to evaluate its performance. The experiment simulated a flight environment of Mach 4 at a 17 km altitude. Magnesium-based solid fuel was used as propellant in this study. The results show that secondary combustion occurs in supersonic combustor. The combustion efficiency of the propellant is about 65%, and the total pressure recovery is about 0.5. These imply that the scramjet configuration using solid fuel as a propellant is feasible. The results of the numerical analysis show that a normal shock wave is generated in the core flow of the combustor, and this is due to all of the fuel-rich gas being injected in the same cross section.