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

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.