| タイトル | Orbit on demand - Structural analysis finds vertical launchers weigh less |
| 著者（英） | Cruz, C. I.; Taylor, A. H.; Wurster, K. E.; Jackson, L. R.; Naftel, J. C.; Cerro, J. A. |
| 著者所属（英） | Kentron International, Inc.|NASA Langley Research Center |
| 発行日 | 1985-02-01 |
| 言語 | eng |
| 内容記述 | Structural considerations arising from favored design concepts for the next generation on-demand launch vehicles are explored. The two emerging concepts are a two stage fully reusable vertical take-off vehicle (V-2) and a horizontal take-off, two stage subsonic boost launch vehicle (H-2-Sub). Both designs have an 1100 n. mi. cross-range capability, with the V-2 orbiter having small wings with winglets for hypersonic trim and the H-2-Sub requiring larger, swept wings. The rockets would be cryogenic, while airbreathing initial boosters would be either turbofans, turbojets and/or ramjets. Dynamic loading is lower in the launch of a V-2. The TPS is a critical factor due to thinner leading edges than on the Shuttle and may require heat-pipe cooling. Airframe structures made of metal matrix composites have passed finite element simulations of projected loads and can now undergo proof-of-concept tests, although whisker-reinforced materials may be superior once long-whisker technology is developed. |
| NASA分類 | SPACECRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 85A24791 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/392757 |
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