| 固液火箭发动机燃烧稳定性试验(英文) |
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| 引用本文： | 张研,汪亮,孙得川,杜新.固液火箭发动机燃烧稳定性试验(英文)[J].固体火箭技术,2010,33(3). |
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| 作者姓名： | 张研 汪亮 孙得川 杜新 |
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| 作者单位： | 西北工业大学,航天学院,西安,710072 |
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| 摘 要： | 针对固液火箭发动机低频非声振荡燃烧问题进行了发动机试验研究。介绍了挤压式过氧化氢(H2O2)-低密度聚乙烯(LDPE)固液火箭发动机试验系统及试验发动机结构特点,并分析了固液火箭发动机不稳定燃烧特点。试验结果表明,通过提高氧化剂供应管路的刚性、改变喷嘴雾化效果,可解决低频振荡燃烧。
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| 关 键 词： | 固液火箭发动机 实验系统 低频振荡燃烧 |
Experimental investigation on combustion stability of hybrid rocket motors |
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| ZHANG Yan,WANG Liang,SUN De-chuan,DU Xin.Experimental investigation on combustion stability of hybrid rocket motors[J].Journal of Solid Rocket Technology,2010,33(3). |
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| Authors: | ZHANG Yan WANG Liang SUN De-chuan DU Xin |
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| Abstract: | The problem of the low-frequency non-acoustic oscillation combustion of the hybrid rocket motor (HRM) was studied. In this paper,the test system of HRM and the structural features of the test motor were also introduced and the unstable combustion features of the HRM were analyzed. The results show that the low-frequency oscillation combustion can be effectively restrained by enhancing the rigidity of oxidizer supply pipeline and improving the nozzle atomization effect. |
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| Keywords: | hybrid rocket motor (HRM) test system low-frequency oscillation combustion |
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