| 考虑燃烧过程的航天器用液体火箭发动机动态特性分析 |
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| 引用本文： | 陈新华,李伟榕.考虑燃烧过程的航天器用液体火箭发动机动态特性分析[J].科学技术与工程,2010,10(11). |
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| 作者姓名： | 陈新华 李伟榕 |
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| 作者单位： | 1. 装备指挥技术学院,北京,101416
2. 太原卫星发射中心,太原,036300 |
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| 摘 要： | 研究了考虑惯性等因素的集液腔充填过程以及考虑喷雾燃烧的发动机动态特性数学模型的建立,结合发动机的喷雾燃烧过程以及燃烧室的集中参数模型,分析了航天器用双组元(一甲基肼/四氧化二氮)液体火箭发动机推力室的脉冲工作特性、启动特性以及关机特性。
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| 关 键 词： | 航天器 液体火箭发动机 启动特性 关机特性 |
| 收稿时间： | 2010/1/22 0:00:00 |
| 修稿时间： | 1/27/2010 7:20:38 PM |
Analysis of Spacecraft Liquid Propellant Rocket Engine Dynamic characteristic for considering Spray Combustion |
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| chenxinhua and Li Weirong.Analysis of Spacecraft Liquid Propellant Rocket Engine Dynamic characteristic for considering Spray Combustion[J].Science Technology and Engineering,2010,10(11). |
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| Authors: | chenxinhua and Li Weirong |
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| Institution: | Institute of Command and Technology of Equipment/a>;Beijing 101416/a>;P.R China/a>;Taiyuan Satellite Launch Center1/a>;Taiyuan 036300/a>;P.R China |
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| Abstract: | The mathematic model of injector cavity filling under the condition of considering inertial factor and the bi-propellant liquid rocket engine's dynamics characteristic model which integrates the supplying pipeline model are created.Associated the spray combustion model and the lumped parameter model of chamber,analyze the pulse work characteristic,the starting characteristic,the shutdown characteristic of the spacecraft bipropellant (MMH/NTO) liquid rocket engine. |
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| Keywords: | spacecraft liquid propellant rocket engine starting characteristic shutdown characteristic |
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