The translational velocity increment, stabilization and control requirements, vehicle weight, and geometric considerations of the Multimission Modular Spacecraft (MMS) provided the basic of the hydrazine propulsion modules. The Landsat D was used as the mission model. Tradeoff studies were conducted on thrust level, thruster location, and clustering arrangement togehter with tankage volume and location. The impact of the use of single and dual seat thruster valves on plumbing configuration, reliability, and overall system cost was studied in detail. Conceptual designs of a recommended propulsion module configuration for both the Delta 3910 and Shuttle were prepared.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Analysis and design study of the multimission modular spacecraft hydrazine propulsion module


    Weitere Titelangaben:

    Analyse und Konstruktionsstudie eines wiederverwendbaren Hydrazinantriebes fuer Raumfahrzeuge


    Beteiligte:
    Etheridge, F.G. (Autor:in) / Woodrift, W.L. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1978


    Format / Umfang :

    8 Seiten, 11 Bilder, 5 Tabellen, 3 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch