@article{oai:jaxa.repo.nii.ac.jp:00031834,
 author = {岩間, 彬 and 青柳, 鐘一郎 and 祖父江, 照雄 and 山崎, 毅六 and IWAMA, Akira and AOYAGI, Shoichiro and SOFUE, Teruo and YAMAZAKI, Kiroku},
 issue = {2_B},
 journal = {東京大学宇宙航空研究所報告},
 month = {Jun},
 note = {固体推進剤の燃焼速度抑制触媒として有用なハロゲン化合物が燃焼安定性におよぽす影響を,小型ロケットモータ地上燃焼実験によって検討した.これらの添加物を含むポリウレタン～過塩素酸アンモニウム系推進剤は,モータのL/Dが17以上の場合,作動圧力がある限界を越えると,音響的不安定燃焼を発生することが見出された.その振動燃焼はロケットモータの軸方向を伝ぱする長さ方向のモードである.SSR 3/4モータ(グレイン寸法100mmφ×1,700 mmL)において,不安定燃焼を起こしたときのガス振動の周波数は約340c/sであった.しかし,SSR1/2および1/4モータでは燃焼速度抑制触媒の量を増やしても,不安定燃焼は発生しない.また,抑制効果が比較的穏やかな別のハロゲン化合物を加えた推進剤は,不安定燃焼を発生する限界作動圧力が上昇する., Test firings of solid propellant rocket were made to study effects of some halides available as the burning rate depressants on the combustion stability. It was noted that polyurethane～ammonium perchlorate-based propellant grains containing these additives caused acoustic combustion instability as the operating pressure increased above a critical value for the motor slender ratio more than 17. The main type of the oscillatory combustion to which these composite propellants are susceptable is the longitudinal mode. Observed frequency of an illustrated pressure oscillation was approximately 340c/s, where there occurred abnormal combustion in SSR 3/4 size motor (the grain of 100mmΦXl,700mmL). However, there has been no occurrence of such an unstable combustion in a motor employing the grain of length to diameter ratio less than 11 at the fixed grain diameter of 100mm even in the case of higher content of the burning rate depressant. Addition of another halide depressant with mild effect to the propellant increases a critical value of the operating pressure above which the motors become unstable., 資料番号: SA0124889000},
 pages = {706--712},
 title = {II.3.4 ポリウレタン : 過塩素酸アンモニウム系推進剤の燃焼安定性におよぼす燃焼速度抑制触媒の影響(3 推進剤)(II.関連研究)},
 volume = {2},
 year = {1966}
}