The objectives of this task were to measure and compare the combustion response characteristics of the selected propellant formulation for the Space Shuttle Advanced Solid Rocket Motor (ASRM) with those of the current Redesigned Solid Rocket Motor (RSRM) formulation. Tests were also carried out to characterize the combustion response of the selected propellant formulation for the ASRM igniter motor.


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    Titel :

    ASRM combustion instability studies


    Beteiligte:
    Strand, L. D. (Autor:in)

    Kongress:

    NATO Advisory Group for Aerospace Research and Development ; 1995 ; Milan, Italy


    Erscheinungsdatum :

    1992-02-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




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