| 高室压脉冲液体火箭发动机特性试验 |
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| 引用本文： | 段毅,刘宇,覃粒子,梁树强,林震. 高室压脉冲液体火箭发动机特性试验[J]. 火箭推进, 2009, 35(2): 12-17 |
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| 作者姓名： | 段毅 刘宇 覃粒子 梁树强 林震 |
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| 作者单位： | 北京航空航天大学宇航学院,北京,100083;北京航空航天大学宇航学院,北京,100083;北京航空航天大学宇航学院,北京,100083;北京航空航天大学宇航学院,北京,100083;北京航空航天大学宇航学院,北京,100083 |
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| 摘 要： | 为了研究高室压脉冲液体火箭发动机工作原理,增压规律以及脉冲特性,通过一系列冷热流试验对试验发动机进行了研究。冷流试验中使用水和氮气作为工质,试验发动机实现自主脉冲工作,验证了差动式可移动活塞应用在推力室中具有增压效果。热流试验中使用气氧/酒精为推进剂,使用传统挤压式推进剂供给系统。在可移动喷注器行程0.8mm条件下,获得9次连续脉冲,燃烧室峰值压强5.511MPa,高于推进剂供给压强（氧气路3.761MPa,酒精路4.424MPa）,表明在相同的推进剂供给压强下,高室压脉冲液体火箭发动机能提高燃烧室压强。
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| 关 键 词： | 脉动燃烧 高室压 差动活塞 可移动喷注器 液体火箭发动机 特性试验 |
Characteristics tests of pulse liquid rocket engine with high chamber pressure |
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| Duan Yi,Liu Yu,Qin Lizi,Liang Shuqiang,Lin Zhen. Characteristics tests of pulse liquid rocket engine with high chamber pressure[J]. Journal of Rocket Propulsion, 2009, 35(2): 12-17 |
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| Authors: | Duan Yi Liu Yu Qin Lizi Liang Shuqiang Lin Zhen |
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| Affiliation: | School of Astronautics;Beijing Univ.of Aeronautics and Astronautics;Beijing 100083;China |
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| Abstract: | Numerous tests using cold flow and hot gas were employed in order to investigate the operating theory,pressurizing principles and pulse characteristics of a Pulse Liquid Rocket Engine(PLRE) with high chamber pressure.A test PLRE with a pressure-fed propellant system was designed and fabricated based on calculations and theoretical analysis.In cold flow tests,water and nitrogen were employed as working substances.The automatic pulse cycles of the test PLRE show that the differential piston increases chamber ... |
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| Keywords: | pulse combustion high chamber pressure differential pistons movable injector liquid rocket engine characteristics tests |
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