Ground Ignition Test of an Orbit Maneuver H/OThruster Based on Gas Dynamic Resonance Igniter

SONG Ya-na; YU Nan-Jia; MA Bin; ZHOU Wen-lu; HUANG Xiang

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Ground Ignition Test of an Orbit Maneuver H/OThruster Based on Gas Dynamic Resonance Igniter

更新时间：2026-07-07

- Ground Ignition Test of an Orbit Maneuver H/OThruster Based on Gas Dynamic Resonance Igniter
- Vol. 20, Issue 3, (2005)
- 作者机构：
  
  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
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2005
- 稿件说明：
移动端阅览
SONG Ya-na, YU Nan-Jia, MA Bin, et al. Ground Ignition Test of an Orbit Maneuver H/OThruster Based on Gas Dynamic Resonance Igniter[J]. 2005, 20(3).
DOI：

SONG Ya-na, YU Nan-Jia, MA Bin, et al. Ground Ignition Test of an Orbit Maneuver H/OThruster Based on Gas Dynamic Resonance Igniter[J]. 2005, 20(3). DOI：

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。

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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Related Institution

School of Astronautics, Beijing University of Aeronautics and Astronautics

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