218206 小型ハイブリッドロケットの燃焼不安定に関する研究(一般04 熱力学・熱工学1)

概要

論文の詳細を見る
Hybrid regression rate theories, based on an idealized turbulent boundary-layer combustion model, were presented by many investigators. On the other hand, there were few theoretical studies on oscillatory combustion in hybrid rocket motors. This paper deals with a theoretical analysis of the low-frequency combustion instability induced by the combustion time lag of liquid oxidizer in small-scale hybrid rocket motors. We obtained the properties of the theoretical stability limit that is determined by the following parameters: the combustion time lag of liquid oxidizer, the residence time of a combustion chamber, injector pressure, chamber pressure, mass flux exponent, O/F, and the polytropic exponent of mixture gas in a combustion chamber. In addition, we conducted some experiments to examine unstable combustion in a hybrid rocket motor. The theoretical stability limit was compared with these experimental data.
2011-03-17