@inproceedings{oai:jaxa.repo.nii.ac.jp:00004907,
 author = {高柳, 大樹 and 鈴木, 俊之 and 藤田, 和央 and Takayanagi, Hiroki 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, In this study, feasibility assessment of a Martian nonstop sample return system as a part of JAXA's future Mars Exploration with Landers and Orbiters (MELOS) mission has been conducted. In the mission scenario, the vehicle enters the Martian atmosphere, collects the Martian dust and atmospheric gases during the hypersonic atmospheric flight, exits the Martian atmosphere, and is inserted into a parking orbit from which a return system departs for the earth. To design aeroshells appropriate for this mission, a parametric study of aeroshells having large ballistic coefficient and moderate lift-to-drag ratio is made. Finally, a baseline design of the aeroshell in sphere-cone form is selected for the Martian aero-flyby sample return system., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064672009, 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のための高弾道係数を有するエアロシェルの検討},
 volume = {JAXA-SP-09-011},
 year = {2010}
}