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  

Ground Ignition Test of an Orbit Maneuver H_2/O_2 Thruster Based on Gas Dynamic Resonance Igniter

作　　者：宋雅娜[1] 俞南嘉[1] 马彬[1] 周文禄 黄翔[2] 

机构地区：[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

出　　处：《航空动力学报》2005年第3期523-528,共6页Journal of Aerospace Power

基　　金：国家863计划资助项目(863-704)

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。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.

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 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程] V433.9