The authors of this paper introduce a new reconstruction technique titled nozzle-throat reconstruction technique to estimate nozzle-throat-erosion history and oxidizer-to-fuel-mass-ratio history in hybrid rockets. Nine static-firing tests were carried out on a 2kN-class cascaded multistage impinging-jet-type hybrid-rocket motor under varying oxidizer-flow rates to evaluate the accuracy of reconstructed results. Nozzle-throat-erosion histories calculated by the nozzle-throat reconstruction technique agreed well with measured values for initial nozzle-throat radius, and successfully reconstructed the case, in which no measurable amount of nozzle-throat erosion occurred. For equivalence ratios 0.6–1.4, the relationship between nozzle-throat-erosion rate and equivalence ratio of reconstructed results displays a trend consistent with chemical-kinetic-limited heterogeneous-combustion theory, as well as predictions made by previous researchers.


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    Titel :

    Method for Determining Nozzle-Throat-Erosion History in Hybrid Rockets


    Beteiligte:
    Kamps, Landon (Autor:in) / Saito, Yuji (Autor:in) / Kawabata, Ryosuke (Autor:in) / Wakita, Masashi (Autor:in) / Totani, Tsuyoshi (Autor:in) / Takahashi, Yusuke (Autor:in) / Nagata, Harunori (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2017-04-17


    Format / Umfang :

    9 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Method for Determining Nozzle Throat Erosion History in Hybrid Rockets

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