연료 Blowing을 고려한 하이브리드 로켓 저주파 불안정성 모델

In this paper, the combustion instabilities which may occur in the hybrid rocket were studied. The mechanism of the "Hybrid low frequency" instability that is considered unique mode in hybrid rocket motor was understanded, and the new hybrid rocekt low frequency instability model with the blowing effect on the fuel surface was suggested. The hybrid rocket propulsion experiments were performed, and the frequencies of the "Hybrid low frequency" instability with this model were predicted with good agreement for the experimental primary pressure oscillaion frequencies. Also this model was compared with the model without the blowing effect and analyzed.