| タイトル | Synchronized Lunar Pole Impact Plume Sample Return Trajectory Design |
| 本文（外部サイト） | http://hdl.handle.net/2060/20160013214 |
| 著者（英） | Foster, Cyrus; Colaprete, Tony; Genova, Anthony L. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 2016-02-15 |
| 言語 | eng |
| 内容記述 | The presented trajectory design enables two maneuverable spacecraft launched onto the same trans-lunar injection trajectory to coordinate a steep impact of a lunar pole and subsequent sample return of the ejecta plume to Earth. To demonstrate this concept, the impactor is assumed to use the LCROSS missions trajectory and spacecraft architecture, thus the permanently-shadowed Cabeus crater on the lunar south pole is assumed as the impact site. The sample-return spacecraft is assumed to be a CubeSat that requires a complimentary trajectory design that avoids lunar impact after passing through the ejecta plume to enable sample-return to Earth via atmospheric entry. |
| NASA分類 | Astrodynamics; Lunar and Planetary Science and Exploration |
| レポートNO | AAS 16-550
ARC-E-DAA-TN32698 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
