| タイトル | Entry Descent and Landing Workshop Proceedings |
| 本文（外部サイト） | http://hdl.handle.net/2060/20170002210 |
| 著者（英） | Dillman, Robert |
| 著者所属（英） | NASA Armstrong Flight Research Center |
| 発行日 | 2015-08-18 |
| 言語 | eng |
| 内容記述 | Entry mass at Mars is limited by the payload size that can be carried by a rigid capsule that can fit inside the launch vehicle fairing. Landing altitude at Mars is limited by ballistic coefficient (mass per area) of entry body. Inflatable technologies allow payload to use full diameter of launch fairing, and deploy larger aeroshell before atmospheric interface, landing more payload at a higher altitude. Also useful for return of large payloads from Low Earth Orbit (LEO). |
| NASA分類 | Spacecraft Design, Testing and Performance |
| レポートNO | DFRC-E-DAA-TN28396-4 |
| 権利 | No Copyright |
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