@inproceedings{oai:jaxa.repo.nii.ac.jp:00004743,
 author = {鈴木, 俊之 and 藤田, 和央 and 酒井, 武治 and 奥山, 圭一 and 加藤, 純郎 and 西尾, 誠司 and Suzuki, Toshiyuki and Fujita, Kazuhisa and Sakai, Takeharu and Okuyama, Keiichi and Kato, Sumio and Nishio, Seiji},
 book = {宇宙航空研究開発機構特別資料: 第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 論文集, JAXA Special Publication: Proceedings of 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010},
 month = {Feb},
 note = {第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 (2010年6月24日-25日. 米子コンベンションセンター BiG SHiP), 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 (June 24-25,  2010. Yonago Convention Center BiG SHiP), Yonago, Tottori Japan, Cloth-layered carbon fiber reinforced plastic ablator with a specific gravity of about 1.5 is developed to examine the prediction accuracy of analysis methods associated with the thermal response of ablator. Heating tests are carried out in the arcjet wind tunnel to quantify the thermal performance of ablator so developed. In the tests, the surface temperatures and in-depth temperatures of ablative test pieces are measured during the testing. The experimental results obtained in the heating tests are analyzed by using a two-dimensional analysis method developed earlier. In the method, the thermal response of ablator is calculated by loosely coupling the shock layer computational fluid dynamics code and the 2-D version of ablation code using an arcjet freestream condition. The arcjet freestream condition in the test section is evaluated by calculating the flows in the arcjet wind tunnel fully theoretically. The present analyses are made especially focusing on an anisotropic nature of thermal conduction of ablator. Thermal conduction inside the ablator is modeled in the code based on measured thermal conductivity values for different ply angles. By comparing the calculated results with the arcjet data, the prediction accuracy of thermal response models of ablator is discussed., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064967036, レポート番号: JAXA-SP-10-012},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {EFD/CFD融合技術に基づくアブレーション熱防御システム評価手法の研究},
 volume = {JAXA-SP-10-012},
 year = {2011}
}