| 硝酸与固体燃料燃烧性能计算研究 |
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| 引用本文： | 高翔,胡春波,孙得川,何国强,杨玉新.硝酸与固体燃料燃烧性能计算研究[J].固体火箭技术,2006,29(2):117-119. |
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| 作者姓名： | 高翔 胡春波 孙得川 何国强 杨玉新 |
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| 作者单位： | 西北工业大学航天学院,西安,710072;西北工业大学航天学院,西安,710072;西北工业大学航天学院,西安,710072;西北工业大学航天学院,西安,710072;西北工业大学航天学院,西安,710072 |
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| 摘 要： | 建立了固液火箭发动机燃烧性能计算模型,采用一维化学平衡(ODE)方法对以硝酸为氧化剂的固液火箭发动机燃烧性能进行了初步探讨。计算表明,固液火箭发动机的比冲、特征速度和燃烧温度以及燃烧产物组分等与氧化剂和燃料的配比有密切关系,氧化剂与燃料质量配比在3.75附近时,固液火箭发动机内部的温度较高,燃烧产物组分以及特征速度达到最佳状态,比冲最高。
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| 关 键 词： | 固液火箭发动机 硝酸 燃烧性能 化学平衡方法 |
| 文章编号： | 1006-2793（2006）02-0117-03 |
| 收稿时间： | 2005-07-11 |
| 修稿时间： | 2005-10-25 |
Investigation on combustion performances of nitric acid and solid fuel |
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| GAO Xiang,HU Chun-bo,SUN De-chuan,HE Guo-qiang,YANG Yu-xin.Investigation on combustion performances of nitric acid and solid fuel[J].Journal of Solid Rocket Technology,2006,29(2):117-119. |
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| Authors: | GAO Xiang HU Chun-bo SUN De-chuan HE Guo-qiang YANG Yu-xin |
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| Abstract: | A computation model of combustion performances for hybrid rocket motor was derived,and combustion performancesfor hybrid rocket motor taking nitric acid as oxidizer were preliminarily discussed by using one-dimension chemical equilibriummethod(ODE).The calculation results showthat the ratio of oxidizer to fuel is closely related to specific impulse,characteristic ve-locity,combustion temperature and combustion product composition of hybrid rocket motor.When mass ratio of oxidizer to fuel isnear 3.75,the temperature in the hybrid rocket motor is very high,and the combustion product composition and characteristic ve-locity are up to the ideal state,and the specific impulse value is the biggest. |
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| Keywords: | hybrid rocket motor nitric acid combustion performance chemical equilibrium method |
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