| タイトル | Multi-Mission Earth Entry Vehicle: Aerodynamic and Aerothermal Analysis of Trajectory Environments |
| 本文（外部サイト） | http://hdl.handle.net/2060/20140007313 |
| 著者（英） | Fuller, John; Dyakonov, Artem; Trumble, Kerry |
| 発行日 | 2010-06-14 |
| 言語 | eng |
| 内容記述 | Multi-mission Earth Entry Vehicle (MMEEV) is designed to deliver small payloads from space to Earth's surface by flying an uncontrolled ballistic entry, which ends with ground impact. The included range of entry velocities is from 10 to 16 km/s. The range of ballistic coefficients is from 41.94 to 128.74 kg/m2, which insures a low subsonic terminal velocity on the order of 50 m/sec. The range of entry flight path angles, considered in this analysis is from -5 to -25 degrees. The assessment and parametric characterization of aeroheating and aerodynamic performance of the capsule during entry is the subject of this paper. |
| NASA分類 | Astrodynamics; Spacecraft Design, Testing and Performance |
| レポートNO | ARC-E-DAA-TN1339 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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