@inproceedings{oai:jaxa.repo.nii.ac.jp:00004906,
 author = {鈴木, 俊之 and 藤田, 和央 and Suzuki, Toshiyuki and Fujita, Kazuhisa},
 book = {宇宙航空研究開発機構特別資料: 第41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2009論文集, JAXA Special Publication: Proceedings fo 41st Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2009},
 month = {Feb},
 note = {平成21年6月18-19日. 宇宙航空研究開発機構調布航空宇宙センター, 18 June-19 June, 2009, Japan Aerospace Exploration Agency, Conceptual study of ablative thermal protection system is made preliminary toward sample return mission by aero fly-by on Mars. Thermal protection system material considered in this study consists of a light-weight ablator, a felt insulator, and CFRP/aluminum honeycomb sandwich panel. A thickness and weight of thermal protection system material required for an atmospheric entry flight on Mars is estimated by calculating a thermal response of ablator along the entry trajectory. The thermal protection system that consists of the ablative material of 25mm thickness and the felt insulator of 20mm thickness is recommended for the present entry trajectory, resulting in the weight ratio of 16% for thermal protection system., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064672008, レポート番号: JAXA-SP-09-011},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {火星エアロフライバイによるサンプルリターンミッションに向けたアブレ－ション熱防御システムの検討},
 volume = {JAXA-SP-09-011},
 year = {2010}
}