| 固冲发动机设计点性能迭代计算(英文) |
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| 引用本文： | 霍东兴,何国强,陈林泉,李岩芳.固冲发动机设计点性能迭代计算(英文)[J].固体火箭技术,2010,33(4). |
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| 作者姓名： | 霍东兴 何国强 陈林泉 李岩芳 |
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| 作者单位： | 1. 西北工业大学,航天学院,西安,710072
2. 中国航天科技集团公司四院四十一所,西安,710025 |
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| 摘 要： | 固冲发动机热力学性能参数计算是发动机性能计算的重要部分,通常是针对特定的推进剂建立热力学数据表格,然后通过插值取得相应参数。通过对NASA CEA程序进行二次开发,使其成为便于应用的子程序,并以补燃室热力计算为基础,通过给定推进剂配方、进气道总压恢复系数、补燃室燃烧效率、比冲效率等设计参数,建立了满足总体推力要求的固冲发动机设计点性能迭代计算方法,为固冲发动机方案设计提供了一种实用工具。
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| 关 键 词： | 固冲发动机 性能计算 设计点 热力计算 |
Iterative calculations for solid rocket ramjet performances on design condition |
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| HUO Dong-xing,HE Guo-qiang,CHEN Lin-quan,LI Yan-fang.Iterative calculations for solid rocket ramjet performances on design condition[J].Journal of Solid Rocket Technology,2010,33(4). |
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| Authors: | HUO Dong-xing HE Guo-qiang CHEN Lin-quan LI Yan-fang |
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| Abstract: | Thermodynamic parameters calculations are one of the important parts for solid rocket ramjet(SRR) performance analysis. Commonly,the parameters are obtained by means of interpolation from data tables which is established for specified propellant.NASA CEA program is secondary-developed successfully to a subroutine.Based on the afterburner thermodynamic calculations,the iterative algorithm for solid rocket ramjet performance on design point is investigated.The propellant composition,air inlet total pressure recovery coefficient,combustion efficiency,and nozzle impulse efficiency are assumed according to experiment.The iterative algorithm is an utility software for SRR scheme design. |
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| Keywords: | solid rocket ramjet performance calculation design condition thermodynamic analysis |
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