There are few experimental studies on rotating detonation engines (RDEs) with liquid propellants. This study reveals the static thrust performance of a cylindrical RDE with ethanol and liquid nitrous oxide as propellants under atmospheric pressure. This RDE had an inner diameter of 40 mm, a maximum combustor length of 230 mm, a nozzle contraction ratio of 1.7, and a nozzle expansion ratio of 9.1. Nineteen experiments were conducted at total mass flow rates of 184 210    g / s , mixture ratios of 3.6–5.9, and combustion pressures of 0.35–0.46 MPa, resulting in a maximum detonation velocity of 1840    m / s (approximately 80% of the theoretical detonation velocity, 2251    m / s ), maximum thrust at sea level of 294 N, and maximum specific impulse at sea level of 148 s. In addition, the maximum characteristic exhaust velocity, c * , was 1716    m / s , which was 99% of the theoretical value. The characteristic length of the combustion chamber at this time was 0.15 m. Since conventional rocket combustion requires 1.57 m to achieve the same c * efficiency, this study shows that detonation combustion can reduce the combustor size by 88%.


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    Titel :

    Nitrous Oxide/Ethanol Cylindrical Rotating Detonation Engine for Sounding Rocket Space Flight


    Beteiligte:
    Ishihara, Kazuki (Autor:in) / Sato, Tomoki (Autor:in) / Kimura, Tomoaki (Autor:in) / Nakajima, Kosuke (Autor:in) / Nakata, Kotaro (Autor:in) / Itouyama, Noboru (Autor:in) / Kawasaki, Akira (Autor:in) / Matsuoka, Ken (Autor:in) / Matsuyama, Koichi (Autor:in) / Kasahara, Jiro (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.01.2025




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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