著者

奥山 圭一 加藤 純郎 山田 哲哉

出版者

宇宙航空研究開発機構

雑誌

宇宙航空研究開発機構研究開発報告 (ISSN:13491113)

巻号頁・発行日

vol.4, pp.55-75, 2005-03

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REV was the first reentry capsule developed through pure domestic technology and successfully recovered. REV is thermally protected against the severe aerodynamic heating by carbon-phenolic ablator material. The present paper describes the feature of the heating test in the arc windtunnel and the ablator characteristics clarified during the research and development process of the REV heatshield. Because the heat flux anticipated on the stagnation surface is about 2 MW/m^2, the dominant surface recession mechanism is identified to be in the reaction control region. The thermochemical reaction data have been acquired through three arc-heater facilities with different enthalpy level for calibration and tuning of the ablation analysis code. The thermomechanical behavior of the ablator under the high heat flux environment such as delamination, or spallation also has been investigated for functional safety of the heatshield.