@inproceedings{oai:jaxa.repo.nii.ac.jp:00014424,
 author = {藤田, 和央 and 鈴木, 俊之 and 高柳, 大樹 and 加納, 希生 and 久保田, 孝 and 尾川, 順子 and 森本, 睦子 and 山田, 哲哉 and 川口, 淳一郎 and Fujita, Kazuhisa and Suzuki, Toshiyuki and Takayanagi, Hiroki and Kano, Kiyo and Kubota, Takashi and Ogawa, Naoko and Morimoto, Mutsuko and Yamada, Tetsuya and Kawaguchi, Junichiro},
 book = {宇宙航行の力学シンポジウム, Symposium on Flight Mechanics and Astrodynamics},
 month = {Dec},
 note = {宇宙航行の力学シンポジウム(平成20年度)(2008年12月4～5日、宇宙航空研究開発機構宇宙科学研究本部), Symposium on Flight Mechanics and Astrodynamics 2008 (December 4-5, 2008. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)), Sagamihara, Kanagawa Japan, Feasibility assessment of the aeroassist system applied to JAXA's future Martian Exploration has been made. The aerobraking technology was found to bring about an increase in the payload ratio by considerable reduction of the propellant mass required for orbital descent after propulsive orbital insertion. The aerocapture technology, if accuracy in both the interplanetary orbit determination and the guidance is improved, was shown to achieve a remarkable increase of the payload mass. The guided entry technologies which realize better landing mark precision than obtained by ballistic flights were proposed. Conceptual study of an aero-flyby sample return system was made as an extended application of the aerocapture technology., 資料番号: AA0064729001},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {次期火星探査へ用いるエアロアシスト誘導技術の検討},
 volume = {平成20年度},
 year = {2009}
}