N₂O自己加圧式供給系を用いたハイブリッドロケットの騒音特性

抄録

Since a rocket engine exhaust has a high Mach number and a high temperature, it is difficult to predict accurately acoustic characteristics. In this paper, we experimentally evaluated the acoustic characteristics of a hybrid rocket using N₂O self-pressurizing system. The sound power generated by the rocket engine was directly proportional to the cube of the effective exhaust velocity. The sound has dominant frequency of 100 Hz and 1300 Hz in the directions of 90 degree. During the firing of the hybrid rocket engine, two directional peaks of the sound pressure level were observed in the directions of 40 degree and 70 degree.