The feasibility and application of a solid propulsion powered spacecraft concept to implement high-energy missions independent of multiplanetary swingby opportunities are assessed. The characteristics of suitable missions and spacecraft were formulated to determine their effects upon propulsion system selection and design. A cost-effectiveness analysis was conducted to provide a meaningful basis of comparing candidate designs. The results substantiated the feasibility of the powered spacecraft concept when used in conjunction with several intermediate-sized launch vehicles as well as energy margins by which to exploit extended mission capabilities. An outgrowth of this study included a new high-mass-fraction solid motor staging design whose performance predictions further enhanced the candidacy of the baseline configuration.


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    Title :

    Solid propulsion powered spacecraft concept.


    Contributors:

    Conference:

    Joint Propulsion Specialist Conference ; 1972 ; New Orleans, LA, US


    Publication date :

    1972-11-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :