To create a new flyable detonation propulsion system, a detonation engine system (DES) that can be stowed in sounding rocket S-520-31 has been developed. This paper focused on the first flight demonstration in the space environment of a DES-integrated rotating detonation engine (RDE) using S-520-31. The flight result was compared with ground-test data to validate its performance. In the flight experiment, the stable combustion of the annulus RDE with a plug-shaped inner nozzle was observed by onboard digital and analog cameras. With a time-averaged mass flow of 182 ± 11    g / s and an equivalence ratio of 1.2 ± 0.2 , the RDE generated a time-averaged thrust of 518 N and a specific impulse of 290 ± 18    s , which is almost identical to the ideal value of constant pressure combustion. Due to the RDE combustion, the angular velocity increased by 5.7    deg / s in total, and the time-averaged torque from the rotational component of the exhaust during 6 s of operation was 0.26    N m . The high-frequency sampling data identified the detonation frequency during the recorded time as 20 kHz in the flight, which was confirmed by the DES ground test through high-frequency sampling data analysis and high-speed video imaging.


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    Titel :

    Space Flight Demonstration of Rotating Detonation Engine Using Sounding Rocket S-520-31


    Beteiligte:
    Goto, Keisuke (Autor:in) / Matsuoka, Ken (Autor:in) / Matsuyama, Koichi (Autor:in) / Kawasaki, Akira (Autor:in) / Watanabe, Hiroaki (Autor:in) / Itouyama, Noboru (Autor:in) / Ishihara, Kazuki (Autor:in) / Buyakofu, Valentin (Autor:in) / Noda, Tomoyuki (Autor:in) / Kasahara, Jiro (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2022-10-17


    Format / Umfang :

    13 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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