Hybrid Rocket Firing Experiments at Various Axial–Tangential Oxidizer-Flow-Rate Ratios

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Abstract

A bread board model (BBM) of an Altering-intensity Swirling Flow Type (A-SOFT) hybrid rocket engine was recently developed, and static firing experiments of the BBM were performed under various axial and tangential oxidizer mass flow rates. A-SOFTs are intended to control thrust at an optimal O/F and achieve a high baseline of regression rates with a fixed motor configuration. This is possible by controlling both the oxidizer mass flow rate and effective geometric swirl number. A simple model based on a continuous and monotonic function of oxidizer mass flux and effective geometric swirl number was able to accurately predict performance of experiments conducted on the A-SOFT BBM. The local fuel regression behavior in the axial direction of the A-SOFT BBM was shown to be like that of Swirling Oxidizer Flow Type (SOFT) hybrid rocket engine. Combustion efficiency was evaluated indirectly using equations for the efficiencies of thrust and specific impulse to eliminate errors due to local pressure shifts and the centrifugal force in swirling flows. In most cases, this indirect method compensated for the overestimations of c* efficiency that resulted by directly using chamber pressure data.

Journal

  • Journal of Propulsion and Power

    Journal of Propulsion and Power 35(1), 94-108, 2018-09-24

    American Institute of Aeronautics and Astronautics

Codes

  • NII Article ID (NAID)
    120006557896
  • NII NACSIS-CAT ID (NCID)
    AA10459896
  • Text Lang
    ENG
  • Article Type
    journal article
  • ISSN
    0748-4658
  • Data Source
    IR 
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