For abstract, see overwrapped with a glass-fiber composite that provides strength and protection from handling damage. The resultant tube is lightweight, strong and has a very low thermal flux. Several styles of tubing ranging from 5 to 38 cm in diameter and up to 305 cm long were fabricated and tested at operating temperatures from 294 to 21 K and operating pressures up to 259 N/sq cm. The primary objective for the smaller sizes was thermal performance optimization of the propulsion system while the primary objective of the larger sizes was weight optimization and to prove fabricability. All major program objectives were met resulting in a design concept that is adaptable to a wide range of aerospace vehicle requirements. Major items of development included: bonding large diameter aluminum end fittings to the thin Inconel liner; fabrication of a 38 cm diameter tube from 0.008 cm thick Inconel; and evaluation of tubing which provides essentially zero quality propellant in a very short period of time resulting in a lower mass of propellant expended in chilldown. (Author)


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    Titel :

    Composite Propulsion Feedlines for Cryogenic Space Vehicles, Volume 2: Appendices


    Beteiligte:
    C. A. Hall (Autor:in) / D. J. Laintz (Autor:in) / J. M. Phillips (Autor:in)

    Erscheinungsdatum :

    1973


    Format / Umfang :

    176 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Composite propulsion feedlines for cryogenic space vehicles, Volume 2: Appendices

    Hall, C. A. / Laintz, D. J. / Phillips, J. M. | NTRS | 1973


    Composite propulsion feedlines for cryogenic space vehicles, volume 1

    Hall, C. A. / Laintz, D. J. / Phillips, J. M. | NTRS | 1973


    Composite Propulsion Feedlines for Cryogenic Space Vehicles, Volume 1

    C. A. Hall / D. J. Laintz / J. M. Phillips | NTIS | 1973