| 基于气动谐振点火器的氢氧变轨火箭发动机地面点火试验 |
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| 引用本文： | 宋雅娜,俞南嘉,马彬,周文禄,黄翔.基于气动谐振点火器的氢氧变轨火箭发动机地面点火试验[J].航空动力学报,2005,20(3):523-528. |
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| 作者姓名： | 宋雅娜 俞南嘉 马彬 周文禄 黄翔 |
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| 作者单位： | 1. 北京航空航天大学,宇航学院,北京,100083
2. 北京航天动力研究所,北京,100076 |
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| 基金项目： | 国家863计划资助项目(863-704) |
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| 摘 要： | 结合气动谐振点火器进行头部设计的氢氧变轨火箭发动机是一项新颖化学火箭推进技术,尤其适于空间站应用。在对适用于发动机头部结构方案的同轴氢氧谐振点火器进行大量特性试验研究的基础上,先后成功进行了发动机头部点火,发动机整体的单脉冲、双脉冲以及3.0s稳定燃烧几种工作状态下的多次试车试验,研制出满足相关技术要求的发动机地面试车样件。
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| 关 键 词： | 航空、航天推进系统 液体火箭发动机 变轨控制 气动加热 点火试验 |
| 文章编号： | 1000-8055(2005)03-0523-06 |
| 收稿时间： | 2004/6/28 0:00:00 |
| 修稿时间： | 2004年6月28日 |
Ground Ignition Test of an Orbit Maneuver H2/O2 Thruster Based on Gas Dynamic Resonance Igniter |
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| SONG Ya-n,YU Nan-Ji,MA Bin,ZHOU Wen-lu and HUANG Xiang.Ground Ignition Test of an Orbit Maneuver H2/O2 Thruster Based on Gas Dynamic Resonance Igniter[J].Journal of Aerospace Power,2005,20(3):523-528. |
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| Authors: | SONG Ya-n YU Nan-Ji MA Bin ZHOU Wen-lu and HUANG Xiang |
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| Institution: | SONG Ya-na~1,YU Nan-Jia~1,MA Bin~1,ZHOU Wen-lu~2,HUANG Xiang~2 |
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| Abstract: | Orbit maneuver hydrogen-oxygen thruster based on gas dynamic resonance igniter is a novel chemical propulsion technology especially prospective in space station application.Through large amounts of experimental investigation on adopted coaxial hydrogen-oxygen resonance igniter features,the thruster head ignition as well as thruster ground test were successfully conducted.The thruster ground tests included single-impulse,double-impulse and 3.0 seconds sustained run.Based on these ignition experiments and tests,thruster that met the proposed technical targets was developed. |
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| Keywords: | aerospace propulsion system liquid propellant rocket engine orbit control aerodynamic heating ignition test |
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