Computations of a new hydrogen-oxygen rocket engine based on supermulti-jets colliding with pulse

Remi Konagaya, Ken Naitoh, Takuma Okamoto, Kohta Tsuru

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    2 Citations (Scopus)

    Abstract

    We propose a new type of rocket engine that uses the new compressive combustion principle based on supermulti-jets colliding with pulse, which may further improve the thermal efficiency of present rocket engines. In this research, we calculate the flow inside the combustion chamber of our new rocket engine by computation, based on the unsteady three-dimensional compressible Navier-Stokes equation, by using a method alike the C-CUP method. Computational results showed that auto-ignition occurred near the center of the chamber, and the pressure of the combustion chamber increased to 3-6 times the value of fuel tanks.

    Original languageEnglish
    Title of host publicationAIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
    PublisherAmerican Institute of Aeronautics and Astronautics Inc.
    ISBN (Electronic)9781624104473
    DOIs
    Publication statusPublished - 2017
    Event55th AIAA Aerospace Sciences Meeting - Grapevine, United States
    Duration: 2017 Jan 92017 Jan 13

    Other

    Other55th AIAA Aerospace Sciences Meeting
    CountryUnited States
    CityGrapevine
    Period17/1/917/1/13

    ASJC Scopus subject areas

    • Aerospace Engineering

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  • Cite this

    Konagaya, R., Naitoh, K., Okamoto, T., & Tsuru, K. (2017). Computations of a new hydrogen-oxygen rocket engine based on supermulti-jets colliding with pulse. In AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting [AIAA 2017-1780] American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2017-1780