Ground Ignition Test of an Orbit Maneuver H<SUB>2</SUB>/O<SUB>2</SUB> Thruster Based on Gas Dynamic Resonance Igniter

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

Volume 20 Issue 3

Jun. 2005

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SONG Ya-na, YU Nan-Jia, MA Bin, ZHOU Wen-lu, HUANG Xiang. Ground Ignition Test of an Orbit Maneuver H2/O2 Thruster Based on Gas Dynamic Resonance Igniter[J]. Journal of Aerospace Power, 2005, 20(3): 523-528.

Citation:

SONG Ya-na, YU Nan-Jia, MA Bin, ZHOU Wen-lu, HUANG Xiang. Ground Ignition Test of an Orbit Maneuver H₂/O₂ Thruster Based on Gas Dynamic Resonance Igniter[J]. Journal of Aerospace Power, 2005, 20(3): 523-528.

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Ground Ignition Test of an Orbit Maneuver H₂/O₂ Thruster Based on Gas Dynamic Resonance Igniter

1.
School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing100083,China
2.
Beijing Aerospace Propulsion Institute,Beijing100076,China

Received Date: 2004-06-28
Rev Recd Date: 2004-09-01
Publish Date: 2005-06-28

Abstract

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.
- aerospace propulsion system,
- liquid propellant rocket engine,
- orbit control,
- aerodynamic heating,
- ignition test