A Thrust generation model of a microwave rocket

マイクロ波ロケットにおける推力生成モデル

小田 靖久*; 柴田 鉄平*; 小紫 公也*; 高橋 幸司; 春日井 敦; 坂本 慶司

Oda, Yasuhisa*; Shibata, Teppei*; Komurasaki, Kimiya*; Takahashi, Koji; Kasugai, Atsushi; Sakamoto, Keishi

マイクロ波ロケットにおける推力は、大気プラズマに起因する衝撃波の伝播によって説明ができる。このパルス爆轟モデルの実験的検証のために、プラズマ圧力の時間変化を調べた。その結果、衝撃波の伝播時間と伝播距離の間には線形関係があることがわかった。また、プラズマ伝播速度は、伝播している間は一定であることも判明した。さらに、両者の速度は、音速程度で伝播することを明らかにした。

A thrust generation model for microwave rocket was studied. The model was based on shock wave propagation driven by atmospheric plasma as analogy of pulse detonation engine (PDE). Pressure histories in the thruster were measured using pressure gauges and compared to the model. The shock wave was measured from pressure history in the thruster model. The relationship between the shock-wave traveling time and propagation distance showed good linearity. At the same time, the propagation velocity of the ionization front in the tube was also measured. The velocity is also nearly constant during the propagation. The both velocities were increased with the power density. The both the ionization front and the shock wave propagated at the same velocity when they propagated at supersonic speed. Thrust impulse was estimated from pressure history. Estimated thrust showed good agreement to the result of the flight experiment.