| タイトル | Heated-Atmosphere Airship for the Titan Environment: Thermal Analysis |
| 本文（外部サイト） | http://hdl.handle.net/2060/20120012527 |
| 著者（英） | Hepp, A. F.; Landis, G. A.; Colozza, A. J.; Heller, R. S. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2012-07-01 |
| 言語 | eng |
| 内容記述 | Future exploration of Saturn's moon Titan can be carried out by airships. Several lighter-than-atmosphere gas airships and passive drifting heated-atmosphere balloon designs have been studied, but a heated-atmosphere airship could combine the best characteristics of both. This work analyses the thermal design of such a heated-atmosphere vehicle, and compares the result with a lighter-than-atmosphere (hydrogen) airship design. A design tool was created to enable iteration through different design parameters of a heated-atmosphere airship (diameter, number of layers, and insulating gas pocket thicknesses) and evaluate the feasibility of the resulting airship. A baseline heated-atmosphere airship was designed to have a diameter of 6 m (outer diameter of 6.2 m), three-layers of material, and an insulating gas pocket thickness of 0.05 m between each layer. The heated-atmosphere airship has a mass of 161.9 kg. A similar mission making use of a hydrogen-filled airship would require a diameter of 4.3 m and a mass of about 200 kg. For a long-duration mission, the heated-atmosphere airship appears better suited. However, for a mission lifetime under 180 days, the less complex hydrogen airship would likely be a better option. |
| NASA分類 | Spacecraft Design, Testing and Performance |
| レポートNO | NASA/TM-2012-217639
E-18250 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/241807 |
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