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H-2ロケットフェアリング断熱材のアーク加熱試験
https://jaxa.repo.nii.ac.jp/records/41166
https://jaxa.repo.nii.ac.jp/records/4116649b45027-e34b-4891-9ee5-b2f31b496e24
名前 / ファイル | ライセンス | アクション |
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naltr01181.pdf (3.7 MB)
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|
Item type | テクニカルレポート / Technical Report(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | H-2ロケットフェアリング断熱材のアーク加熱試験 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 断熱材料 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 耐熱材料 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 高温試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | エポキシ樹脂 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 熱特性 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | シリコンゴム | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | TPS | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 熱防御システム | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 熱防御性能試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | アーク加熱風洞試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | よどみ点熱伝達 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | よどみ点加熱率制御 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 熱吸収率 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | H-2ロケット | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | フェアリング | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | heat insurating material | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | heat resisting material | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | high temperature test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | heat resistance characteristic | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | epoxy resin | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | thermal property | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | silicon rubber | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | TPS | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | thermal protection system | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | thermal protection capacity test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | arc heated wind tunnel test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic heating | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | stagnation point heat transfer | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | stagnation point heating rate control | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | heat absorption rate | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||
資源タイプ | technical report | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Arc-heating tests of thermal protection system materials for the H-2 rocket fairing | |||||
著者 |
平林, 則明
× 平林, 則明× 松崎, 貴至× 福島, 幸夫× 中村, 富久× 藤田, 猛× Hirabayashi, Noriaki× Matsuzaki, Takashi× Fukushima, Yukio× Nakamura, Tomihisa× Fujita, Takeshi |
|||||
著者所属 | ||||||
航空宇宙技術研究所 空気力学部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 空気力学部 | ||||||
著者所属 | ||||||
宇宙開発事業団 | ||||||
著者所属 | ||||||
宇宙開発事業団 | ||||||
著者所属 | ||||||
宇宙開発事業団 | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Aerodynamics Division | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Aerodynamics Division | ||||||
著者所属(英) | ||||||
en | ||||||
National Space Development Agency of Japan | ||||||
著者所属(英) | ||||||
en | ||||||
National Space Development Agency of Japan | ||||||
著者所属(英) | ||||||
en | ||||||
National Space Development Agency of Japan | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory (NAL) | |||||
書誌情報 |
航空宇宙技術研究所報告 en : Technical Report of National Aerospace Laboratory 巻 1181, p. 1-22, 発行日 1992-10 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 日本の次世代打ち上げ用ロケットH-2の頭部フェアリングに用いる熱防御システム(TPS)に適した材料をアーク加熱風洞により試験した。候補材料の主なものはエポキシ樹脂とシリコンゴムである。H-2ロケット上昇時の頭部空力加熱の最大値に合せて試験時加熱率は60〜100kW/平方メートルとした。試験結果によれば、TPS主材としては縮合型シリコンゴムが最適で、また、シリカコーティングは欠かすことのできないものである。また、フェアリング頭部の表面温度に関する試験と推算の結果から、熱防御のためのシリカコーティングの厚さは2mmで十分であると思われる。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Materials suitable for the Thermal Protection System (TPS) of the rocket fairing for the Japanese next generation launch vehicle named H-2 were tested using an arc-heated wind tunnel. The main constituents of the candidate materials were epoxy resin and silicon rubber. The heating rate was from 60 to 100 kW/(sq m) in accordance with the maximum heating rate of the nose region of an ascending H-2 rocket. Test results showed that polycondensed silicon rubber was the best candidate as the main component of the TPS, and also that a SiC coating was indispensable. In addition, based on results and a preliminary estimation of the skin temperatures of the fairing nose region, a SiC coating of about two mm in thickness is considered sufficient to achieve thermal protection capability. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0389-4010 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0004196000 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL TR-1181 |