這篇文章是探討有關固體火箭流體轉向對 於燃燒不穩定之影響,這個研究結果顯示聲波 場之存在,造成流場之振盪,而其振盪頻率和聲場 之頻率相同。此流場週期振盪之現象發生於所 有之測試情況;同時,其振盪之現象和聲波之振 幅、頻率,以及聲場之位置有關。這些結果顯 示在固體火箭中流體轉向之趨動或抑制特性和聲波 場之特性有關。 This paper describes results of a numerical study of the effect of the flow turning process upon axial instabilities in a simulated solid rocket motor. Specifically, the flow velocity behavior under different pressure excitations were presented in this paper. These studies revealed that the presence of a pressure oscillation produced oscillatory axial and vertical velocities having the same frequency as the pressure wave for all test frequencies. In addition, this oscillatory flow behavior was observed when the flow turning region was located at a pressure node, a pressure antinode, and in between. The amplitudes and phases of these velocity oscillations depended on the magnitudes and frequencies of the pressure oscillations, and on the temperature of the vertical injected flow. These results suggest that the driving/damping characteristics of the flow turning process would depend on the acoustic characteristics inside the rocket motors.
中國航空太空學會民國八十年學術研討會論文集=Proceedings of the 1991 Aeronautics and Astronautics Conference of the A=eronautical and Astronautical Society of the R.O.C.，頁781-790