Simple control of oxidizer flux for efficient extinction–reignition on a single-stage hybrid rocket

Abstract This study aims at revealing the effect of the simple control of oxidizer flux on a hybrid rocket engine for an efficient extinction–reignition sequence to extend the downrange as well as the duration in the lower thermosphere. The data mining result in the prior study achieved a hypothesis that the thrust control between 1st and 2nd combustions spurs improving extinction–reignition performance. Accordingly, this study simply defines two amounts of oxidizer flux for 1st and 2nd combustions; we investigate using the design informatics platform whether this simple control of oxidizer flux is practically effective to improving extinction–reignition performance. Consequently, oxidizer flux control successfully fulfills the downrange extension as well as the duration protraction as we had expected. Furthermore, the evolutionary multiobjective optimization generates non-simple structure of the feasible region in the design space. Trajectory analyses for signature individuals and a data mining have specified detailed design strategies. In addition, they have also explained physical reasons why the non-simple structure is formed. Extinction–reignition with oxidizer flux control is useful for efficient operations of the hybrid rocket system.

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