| H_2O_2/HTPB缩比固液火箭发动机药柱燃速试验研究 |
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| 引用本文： | 李新田,曾鹏,田辉,蔡国飙.H_2O_2/HTPB缩比固液火箭发动机药柱燃速试验研究[J].固体火箭技术,2011(4). |
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| 作者姓名： | 李新田 曾鹏 田辉 蔡国飙 |
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| 作者单位： | 北京航空航天大学宇航学院; |
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| 摘 要： | 对采用90%H2O2/HTPB基推进剂组合的缩比固液火箭发动机开展了药柱燃速试验研究,得到了不同点火方式和不同氧化剂流率下的药柱燃速。试验结果表明,在相同的氧化剂流率下,催化点火方式比点火药点火方式药柱燃速要高,燃烧室压力更为平稳,同时建压时间要长。根据点火药点火方式下不同氧化剂流率的药柱燃速拟合得到了燃速公式,并运用燃速公式对300 mm全尺寸发动机进行了装药设计及内弹道性能计算,得到的理论性能曲线与试验结果吻合很好,验证了本文采用的燃速研究方法及结果。
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| 关 键 词： | 过氧化氢 固液火箭发动机 燃速 地面试验 |
Experimental study on burning rate of sub-scale H_2O_2/HTPB hybrid rocket motor grain |
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| LI Xin-tian,ZENG Peng,TIAN Hui,CAI Guo-biao.Experimental study on burning rate of sub-scale H_2O_2/HTPB hybrid rocket motor grain[J].Journal of Solid Rocket Technology,2011(4). |
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| Authors: | LI Xin-tian ZENG Peng TIAN Hui CAI Guo-biao |
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| Institution: | LI Xin-tian,ZENG Peng,TIAN Hui,CAI Guo-biao(School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100191,China) |
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| Abstract: | The experimental researches on solid fuel regression rate of sub-scale hybrid rocket motor with the hydrogen peroxide(H2O2)and hydroxyl-terminated polybutadiene(HTPB)-based propellant combination are presented in this paper,and the solid fuel regression rate data under various ignition modes and oxidizer mass flux are carried out.The results show that with catalytic bed ignition mode,the fuel regression rate is higher and the chamber pressure is more stable,but longer chamber pressure build-up time is neede... |
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| Keywords: | hydrogen peroxide hybrid rocket motor fuel regression rate ground test |
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