| タイトル | Earth Entry Vehicle Design for Sample Return Missions Using M-SAPE |
| 本文（外部サイト） | http://hdl.handle.net/2060/20160006414 |
| 著者（英） | Samareh, Jamshid |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2015-06-15 |
| 言語 | eng |
| 内容記述 | Most mission concepts that return sample material to Earth share one common element: an Earth entry vehicle (EEV). The primary focus of this paper is the examination of EEV design space for relevant sample return missions. Mission requirements for EEV concepts can be divided into three major groups: entry conditions (e.g., velocity and flight path angle), payload (e.g., mass, volume, and g-load limit), and vehicle characteristics (e.g., thermal protection system, structural topology, and landing concepts). The impacts of these requirements on the EEV design have been studied with an integrated system analysis tool, and the results will be discussed in details. In addition, through sensitivities analyses, critical design drivers that have been identified will be reviewed. |
| NASA分類 | Spacecraft Design, Testing and Performance |
| レポートNO | NF1676L-21196 |
| 権利 | No Copyright |
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