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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
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)
