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 ) / cm 3 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.


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    Titel :

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


    Beteiligte:
    Baek, Seungkwan (Autor:in) / Jung, Woosuk (Autor:in) / Kang, Hongjae (Autor:in) / Kwon, Sejin (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2018-06-25


    Format / Umfang :

    6 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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