@article{oai:jaxa.repo.nii.ac.jp:00031820,
 author = {植村, 益次 and 砂川, 恵 and 市田, 和夫 and 井山, 尚史 and UEMURA, Masuji and SUNAKAWA, Megumi and ICHIDA, Kazuo and IYAMA, Hisashi},
 issue = {2_B},
 journal = {東京大学宇宙航空研究所報告},
 month = {Jun},
 note = {The nose cones of HT-110 rockets were fabricated of fiberglass reinforced plastics (FRP), which has a high ratio of strength to density, a good heat insulation effect and a high transparency for radar waves. The nose cone and tail fin of rocket are exposed to high temperature due to the aerodynamic heating during the high supersonic flight. When the flight duration is not so long under the condition mentioned above, FRP nose cone can play its role as a structural component even though its thermal resistant characteristics are not so excellent compared with that of refractory metals, and owing to the low heat conductivity of FRP, the temperature at the inside of the nose cone has a little change and the measuring apparatus installed can keep their normal performances. Moreover, the ablation reaction over the surface of the cone is expected to contribute in decreasing the heat transfer coefficient at the aerodynamic heating. In the present paper, the results of measurement of temperature on the FRP nose cone at the flight test of HT-110-2 together with that of the static experiments by use of the rapid radiant heating equipment are reported. The data obtained and some discussions on the results will give a better foundation on the analytical work and could be also effectively utilized for the design of heat resistant structures in the proceeding space program., 資料番号: SA0124875000},
 pages = {570--579},
 title = {II.1.3 強化プラスチックノーズコーンの超音速飛行時の温度と耐熱性について(1 機体および構造)(II.関連研究)},
 volume = {2},
 year = {1966}
}