In order to develop a solid propellant for gas hybrid rocket motor, it is required to investigate the burning characteristics of fuel - rich ammonium perchlorate(AP) based composite propellant. For fuel - rich composite propellant prepared with coarse AP and fine AP, the burning characteristics and the self - quenched combustion were investigated in this study. The following results were obtained : 1) The burning rate decreases as the AP content decreases, and the propellants contained less than a certain AP content self - quench. The self - quenched combustion occurs at a lower pressure and a higher pressure. 2) The lower limit of AP content to combust, Φmin exists. The Φmin of coarse AP is lower than that of fine AP. 3) It was found that the possibility of combustion for AP / HTPB composite propellant was dependent on the AP content, the particle size of AP, and the pressure. 4) The combustion of the propellant was self - quenched when AP particle did not expose on the burning surface. 5) The Φmin was directly independent on the heat generated on the burning surface and the burning rate. It could be considered that Φmin was greatly dependent on the particle size and the distances between two adjacent AP particles.
ハイブリッドロケット用固体推進薬の開発のために, Fuel - rich AP / HTPB系コンポジット推進薬の燃焼特性を明らかにする必要がある｡ 本実験では, 粗粒または微粒APを用いて製造されたFuel - rich AP / HTPB系コンポジット推進薬の燃焼速度特性及び中断燃焼について調べた｡ その結果, 以下のことが明らかになった｡ 1) AP含有率の減少にしたがい燃焼速度は減少し, あるAP含有率以下で中断燃焼が起こった｡ 中断燃焼は低圧または高圧領域から起こった｡ 2) 燃焼可能なAP含有率の下限, Φminが存在した｡ 粗粒APを用いた推進薬のΦminは, 微粒APを用いた推進薬のそれより小さかった｡ 3) AP/HTPB系コンポジット推進薬の燃焼が可能な範囲は, AP含有率, APの粒子径及び圧力に依存することがわかった｡ 4) 燃焼表面にAP粒子が露出しない場合, 推進薬の燃焼は中断することがわかった｡ 5) Φminは燃焼速度と燃焼表面上で発生する熱量には直接的に影響されず, APの粒子径とAP粒子間の距離に大きく依存する。