the Institute of Space and Aeronautical Science University of Tokyo
the Institute of Space and Aeronautical Science University of Tokyo
the Institute of Space and Aeronautical Science University of Tokyo
出版者
東京大学宇宙航空研究所
雑誌名
東京大学宇宙航空研究所報告
巻
2
号
2_B
ページ
580 - 584
発行年
1966-06
抄録（英）
The structure of the nozzle of the motor of SSR is shown in Fig. 2. Alalloy is capable to be replaced for the steel part in a common conventional design, owing to the good effect of insulator between the graphite of the throat and the Al-alloy casing. By replacement of material the nozzle structure reduces its weight to about 50% in comparison with the conventional design. Furthermore, we tested the new design in which we replaced the FRP for the Alalloy. By this new replacement of FRP the nozzle structure reduced its weight to 36% in comparison with the convention design. However in the actual flying test rocket the nozzle of former type is used to expedite the project instead of using the last type.
II.1.4 SSRロケットのノズル構造について(1 機体および構造)(II.関連研究)
SA0124876.pdf
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