Development of High-Performance Green-Monopropellant Thruster with Hydrogen Peroxide and Ethanol

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Green liquid monopropellant thrusters provide an alternative to toxic hydrazine. A premixed liquid monopropellant based on hydrogen peroxide with ethanol blending was suggested to replace hydrazine in this research. The maximum theoretical vacuum specific impulse was 282 s for a certain mixture ratio. A 10-N-scale monopropellant thruster was used for performance evaluation. Platinum with porous gamma-phase alumina support was used as a catalyst. A preliminary firing test was performed for 5 s with propellant A, which had 181 s of vacuum specific impulse. Catalytic combustion occurred without an additional igniter with 87.7% of C∗ efficiency in a preliminary firing test. Propellant B, which had 214 s of vacuum specific impulse and 276  (g⋅s)/cm3 of vacuum density specific impulse, was selected as an alternative to hydrazine. A thruster firing test was performed for 5 s, the C∗ efficiency was measured as 95.3%, and the chamber-pressure oscillation was approximately ±13%. To reduce combustion instability, lanthanum hexaaluminate (a high-thermal-resistant catalyst support) was applied in an additional firing test. The pressure oscillation was measured as ±3.8%, with 92.8% of C∗ efficiency in an additional firing test. These results demonstrated the feasibility of an ethanol-blended hydrogen peroxide thruster as a high-performance and green-propellant thruster for space missions.
Publisher
AMER INST AERONAUTICS ASTRONAUTICS
Issue Date
2018-09
Language
English
Article Type
Article
Citation

JOURNAL OF PROPULSION AND POWER, v.34, no.5, pp.1256 - 1264

ISSN
0748-4658
DOI
10.2514/1.B37081
URI
http://hdl.handle.net/10203/247656
Appears in Collection
AE-Journal Papers(저널논문)
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