| タイトル | A Rigid Mid-Lift-to-Drag Ratio Approach to Human Mars Entry, Descent, and Landing |
| 本文（外部サイト） | http://hdl.handle.net/2060/20160014035 |
| 著者（英） | Theisinger, John E.; Matz, Daniel A.; Campbell, Charles H.; Kinney, David J.; Robinson, Phil; Sostaric, Ronald R.; Stachowiak, Susan J.; Garcia, Joseph A.; Bowles, Jeffrey V.; Cerimele, Christopher J.; Robertson, Edward A.; Johnson, Breanna J. |
| 著者所属（英） | NASA Johnson Space Center |
| 発行日 | 2017-01-09 |
| 言語 | eng |
| 内容記述 | Current NASA Human Mars architectures require delivery of approximately 20 metric tons of cargo to the surface in a single landing. A proposed vehicle type for performing the entry, descent, and landing at Mars associated with this architecture is a rigid, enclosed, elongated lifting body shape that provides a higher lift-to-drag ratio (L/D) than a typical entry capsule, but lower than a typical winged entry vehicle (such as the Space Shuttle Orbiter). A rigid Mid-L/D shape has advantages for large mass Mars EDL, including loads management, range capability during entry, and human spaceflight heritage. Previous large mass Mars studies have focused more on symmetric and/or circular cross-section Mid-L/D shapes such as the ellipsled. More recent work has shown performance advantages for non-circular cross section shapes. This paper will describe efforts to design a rigid Mid-L/D entry vehicle for Mars which shows mass and performance improvements over previous Mid-L/D studies. The proposed concept, work to date and evolution, forward path, and suggested future strategy are described. |
| NASA分類 | Spacecraft Design, Testing and Performance |
| レポートNO | JSC-CN-37857 |
| 権利 | No Copyright |
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