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.


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    Titel :

    Orbit on demand - Structural analysis finds vertical launchers weigh less


    Beteiligte:
    Taylor, A. H. (Autor:in) / Cruz, C. I. (Autor:in) / Jackson, L. R. (Autor:in) / Naftel, J. C. (Autor:in) / Wurster, K. E. (Autor:in) / Cerro, J. A. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1985-02-01



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch







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