The applicability of solid-propellant rockets into a regime of high-performance long-burning tasks beyond the capability of existing motors is discussed. Successful static test firings have demonstrated the feasibility of: (1) utilizing fully case- bonded end-burning propellant charges without mechanical stress relief; (2) using an all-carbon radiative nozzle markedly lighter than the flight-weight ablative nozzle it replaces, and (3) producing low spacecraft acceleration rates during the thrust transient through a controlled-flow igniter that promotes operation below the previous combustion limit. (Author)


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    Titel :

    Solid-Propellant Motors for High-Incremental-Velocity Low-Acceleration Maneuvers in Space


    Beteiligte:
    J. I. Shafer (Autor:in)

    Erscheinungsdatum :

    1972


    Format / Umfang :

    95 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch