@inproceedings{oai:jaxa.repo.nii.ac.jp:00003654,
 author = {鈴木, 俊之 and 滝沢, 直美 and 青木, 卓哉 and 石田, 雄一 and 小笠原, 俊男 and 渡邉, 泰秀 and 藤田, 和央 and Suzuki, Toshiyuki and Takizawa, Naomi and Aoki, Takuya and Ishida, Yuichi and Ogasawara, Toshio and Watanabe, Yasuhide and Fujita, Kazuhisa},
 book = {宇宙航空研究開発機構特別資料: 第47回流体力学講演会/第33回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 47th Fluid Dynamics Conference / the 33rd Aerospace Numerical Simulation Symposium},
 month = {Mar},
 note = {第47回流体力学講演会/第33回航空宇宙数値シミュレーション技術シンポジウム (2015年7月2日-3日. 東京大学生産技術研究所), 目黒区, 東京, 47th Fluid Dynamics Conference /the 33rd Aerospace Numerical Simulation Symposium (July 2-3, 2015. Institute of Industrial Science , the University of Tokyo), Meguro-ku, Tokyo, Japan, Lightweight ablative material has been developed in Japan Aerospace Exploration Agency for Mars rover mission in Japan. Basic thermal characteristics of ablating material are obtained by conducting heating tests in high enthalpy facilities. Thermal  conductivity measurements and thermogravimetry analysis are made to develop a numerical analysis code to predict the thermal performance of ablator in flight environments. Tensile strength tests are carried out to examine the mechanical performance of ablator. Effects of Martin dust storm on the surface erosion of ablator are also investigated experimentally. Finally, a breadboard model of the lightweight ablator aeroshell with the diameter of 500mm is developed to examine a manufacturability of proto flight model of aeroshell. The developed BBM is qualified through vibration tests, pyro shock tests, and thermal-vacuum tests at the qualification test level of the mission requirements., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630005029, レポート番号: JAXA-SP-15-013},
 pages = {183--188},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {火星着陸探査に向けた大気突入モジュールのエアロシェル開発},
 volume = {JAXA-SP-15-013},
 year = {2016}
}