新颖机动变轨化学火箭发动机头部研究  

Investigation on head of novel chemical thruster for orbit maneuver

作　　者：宋雅娜[1] 张国舟[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：《北京航空航天大学学报》2005年第8期888-892,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家 8 63计划资助项目 (863 70 4)

摘　　要：为研究轻型、可靠、环保的空间站机动变轨发动机,在氢 氧液体火箭发动机头部设计中引入了新型气动谐振点火技术.结合发动机推力室设计以及同轴氢氧谐振点火器研究,确定了用富燃的谐振点火火炬与剩余主体氧气再燃烧的发动机头部整体方案.通过对几种主氧喷嘴下发动机头部结构方案研究,选定了主氧喷嘴结构形式.针对发动机要求快速起动、点火响应时间短的关键技术,提出了几种研究实现途径,包括谐振加热装置的结构形式优化、参数匹配优化、材料改进以及点火组元进入时序研究等,以提高气动谐振装置的加热速度及点火能量集聚效率,最终实现了发动机起动时间达到0 .2s以内.To develop light, reliable, sanitary space station maneuverable orbital transfer thruster, the novel gas dynamic resonance ignition method was applied. By means of thruster combustor design combined with coaxial hydrogen/oxygen resonance igniter investigation, method of using fuel-rich resonance ignition torch to further combust with the rest main part of oxygen downwards was adopted for the thruster head scheme. Through investigation on schemes of the thruster head configuration, structural schemes of the main oxygen injector were studied and determined. With respect to the key technique of short ignition response for orbital transfer thruster＇ s quick starts, several solving approaches were proposed, including： optimization of the resonance device structure, optimization of matches between the resonance dominating parameters, improvement on materials and timing adjustment of the ignition propellants etc. By greatly increasing its heating speed and energy gathering efficiency of the resonance device,the starting delay of the thruster was restricted in 0. 2 s.

关 键 词：变轨 液体火箭发动机 点火 谐振 

分 类 号：V434.24[航空宇航科学与技术—航空宇航推进理论与工程]