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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    ASRM combustion instability studies

    Strand, L. D. | NTRS | 1992


    ASRM soluble core

    JANSON, E. / BIZZRLL, R. / DANIEWICZ, D. et al. | AIAA | 1993



    ASRM plume deflector analysis program

    DAWSON, MICHAEL / DOUGLAS, III, FREDDIE / ORLIN, PETER | AIAA | 1992


    ASRM Case Insulation development

    TAM, W. / BELL, M. | AIAA | 1993