著者

羽生 宏人 和田 英一 丹羽 崇博 近藤 靖雄 川村 尚史 丸山 信也 岡村 彩乃 山科 早英良 永井 康仁 中道 達也 上道 茜 田中 成明 小林 直樹 笠原 次郎 森田 泰弘

出版者

一般社団法人 日本航空宇宙学会

雑誌

航空宇宙技術 (ISSN:18840477)

巻号頁・発行日

vol.9, pp.15-21, 2010 (Released:2010-05-14)

参考文献数

6

被引用文献数

1

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The educational hybrid-rocket was successfully launched and it also landed within the predicted area. Aerodynamic characteristics of the rocket designed by students of Tsukuba University were evaluated by the wind tunnel testing with the support of Tokai University. The flight path affected by the environmental condition, especially wind direction and velocity, was simulated with the original calculation program. The altitude of the rocket was measured with the optical equipment and the apex was 123 m although the calculation indicated 198 m. We expected that the insufficient filling or the volatilization of Nitrous oxide as an oxidizer led to this result. And then, the apex was verified with a function of the oxidizer filling ratio. The results showed that 81.2 % of the oxidizer volume in comparison with the firing test condition was accumulated in the tank at the launch.

著者

羽生 宏人 和田 英一 丹羽 崇博 近藤 靖雄 川村 尚史 丸山 信也 岡村 彩乃 山科 早英良 永井 康仁 中道 達也 上道 茜 田中 成明 小林 直樹 笠原 次郎 森田 泰弘

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

航空宇宙技術 (ISSN:18840477)

巻号頁・発行日

vol.9, pp.15-21, 2010

被引用文献数

1

---

The educational hybrid-rocket was successfully launched and it also landed within the predicted area. Aerodynamic characteristics of the rocket designed by students of Tsukuba University were evaluated by the wind tunnel testing with the support of Tokai University. The flight path affected by the environmental condition, especially wind direction and velocity, was simulated with the original calculation program. The altitude of the rocket was measured with the optical equipment and the apex was 123 m although the calculation indicated 198 m. We expected that the insufficient filling or the volatilization of Nitrous oxide as an oxidizer led to this result. And then, the apex was verified with a function of the oxidizer filling ratio. The results showed that 81.2 % of the oxidizer volume in comparison with the firing test condition was accumulated in the tank at the launch.