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title熱分解ガスを考慮したアブレータ熱応答に関する研究
Other TitleA study on the ablator thermal response considering pyrolysis gases
Author(jpn)鈴木 俊之; 澤田 恵介; 山田 哲哉; 稲谷 芳文
Author(eng)Suzuki, Toshiyuki; Sawada, Keisuke; Yamada, Tetsuya; Inatani, Yoshifumi
Author Affiliation(jpn)宇宙航空研究開発機構 総合技術研究本部; 東北大学; 宇宙航空研究開発機構 宇宙科学研究本部; 宇宙航空研究開発機構 宇宙科学研究本部
Author Affiliation(eng)Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Tohoku University; Japan Aerospace Exploration Agency Institute of Space and Astronautical Science; Japan Aerospace Exploration Agency Institute of Space and Astronautical Science
Issue Date2005-03
PublisherInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)
宇宙航空研究開発機構宇宙科学研究本部
Publication title宇宙航行の力学シンポジウム 平成16年度
Symposium on Flight Mechanics and Astrodynamics 2004
Start page53
End page56
Publication date2005-03
Languagejpn
AbstractThe pyrolysis gas pressure inside ablative material is investigated experimentally and numerically. First, the gas permeability of the ablative material developed in ISAS is measured in order to improve the SCMA code so that it can give the detailed thermal response of ablator. Next, the measurements of pyrolysis gas pressure inside ablator test piece are attempted in the arc-heated wind tunnel installed in ISAS. It is suggested from the experimental data and the computed result that delamination of ablator likely occurs at the region where ablator is not fully charred but partially pyrolyzed, which results in a smaller porosity and higher pyrolysis gas pressure in the region. Finally, a two-dimensional version of the SCMA code is developed for the purpose of studying thermal response of ablative test piece that is put into the arc-heated airflow. It is found that the maximum pressure value along the centerline of the ablative test piece becomes 1/3 of that obtained by the one-dimensional calculation. It is also indicated in this study that the maximum pressure value can be further reduced if carbon-cloths are properly tilted with respect to the ablating surface.
Keywordsablator thermal response; pyrolysis; delamination; composite material; MUSES-C; thermal protection system; laminate; numerical analysis; numerical simulation; アブレータ熱応答; 熱分解; 層剥離; 複合材料; MUSES-C; 熱防御系; 積層板; 数値解析; 数値シミュレーション
Document TypeConference Paper
JAXA Categoryシンポジウム・研究会
SHI-NOAA0048089014
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/42520


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