To raise the level of understanding of combustion mode transition characteristics in solid rocket scramjet engine, direct connect experiment of mode transition in solid rocket scramjet engine is investigated in this paper. The result shows that under the same inlet flow condition and engine configuration, there may be subsonic combustion mode or supersonic combustion mode, and in other words, hysteresis of combustion mode transition appears. Analyzing the distribution of pressure along the engine during initial ignition stage of experiments, it is found that hysteresis of combustion mode transition is caused by difference in ignition region of fuel gas.
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