This paper discusses analyses which have been conducted on realistic orbital launch booster vehicles utilizing cryogenic propellants. The effect on the design of the cryogenic stages of propellant performance, orbital storage period, and space environment is described, as is the influence of design variations upon the propellant loss rate in orbit of realistic orbital launch boosters. A thermal analysis from boost and transition through orbital conditions is also presented.


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    Titel :

    Orbital Storage of Cryogenic Propellants for Rendezvous Missions


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:
    Taton, J. W. (Autor:in) / Boyles, R. Q. (Autor:in)

    Kongress:

    Pre-1964 SAE Technical Papers ; 1906



    Erscheinungsdatum :

    01.01.1962




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Orbital storage of cryogenic propellants for rendezvous missions

    Boyles, Jr., R.Q. / Tatom, J.W. | Engineering Index Backfile | 1962



    Piloted Mars missions using cryogenic and storable propellants

    Striepe, Scott A. / Desai, Prasun N. | NTRS | 1993


    Piloted Mars Missions Using Cryogenic and Storable Propellants

    Striepe, S. A. / Desai, P. N. / American Astronautical Society et al. | British Library Conference Proceedings | 1993