| 基于热力计算的固体火箭冲压发动机理论性能研究 |
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| 引用本文： | 于宁,杨涛,刘巍,李理.基于热力计算的固体火箭冲压发动机理论性能研究[J].固体火箭技术,2009,32(2). |
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| 作者姓名： | 于宁 杨涛 刘巍 李理 |
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| 作者单位： | 国防科技大学航天与材料工程学院,长沙,410073 |
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| 摘 要： | 研究了固体火箭冲压发动机的理论性能,采用编制的热力计算程序对含铝镁和含硼贫氧推进刺进行了计算,分析了在设计点处补燃室温度、冻结流比冲、平衡流比冲随空燃比变化的趋势,以及比冲随补燃室压强变化的趋势.计算结果表明,冻结流比冲低于平衡流比冲;在合理空燃比区内,选取空燃比作为设计值,有利于提高发动机性能;提高补燃室压强和选用高能推进剂都能有效提高比冲,但补燃室压强的提高受进气道设计的制约.
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| 关 键 词： | 固体火箭冲压发动机 热力计算 合理空燃比区 比冲 补燃室压强 |
Study on theoretical performance of solid ducted rocket based on thermodynamic calculation |
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| YU Ning,YANG Tao,LIU Wei,LI Li.Study on theoretical performance of solid ducted rocket based on thermodynamic calculation[J].Journal of Solid Rocket Technology,2009,32(2). |
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| Authors: | YU Ning YANG Tao LIU Wei LI Li |
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| Institution: | YU Ning,YANG Tao,LIU Wei,LI li (College of Aerospace and Material Engineering,NUDT,Changsha 410073,China) |
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| Abstract: | To investigate the theoretical performance of solid ducted rocket(SDR),the performances of aluminum-magnesium and boron-based fuel-rich propellants were calculated.The tendency of change of temperature of afterburning chamber,frozen flow specific impulse and equilibrium flow specific impulse with different air/fuel ration at the design operation point was analyzed. Meanwhile,the tandency of change of specific impulse along with pressure of afterburning chamber were analyzed.The results show that the specifi... |
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| Keywords: | solid ducted rocket thermal calculation reasonable area of air/fuel ratio specific impulse pressure of afterburning chamber |
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