The characteristics of an optimum thrust program depending on the individual mission of a spacecraft propulsion system and the present state-of-art of realization are discussed. Results of additional theoretical and experimental investigations are presented which confirm that arbitrary at least near-optimum thrust profiles may be realized with solid propellant rockets. In practice, however, overall optimization calls for a compromise between thrust program, structure weight, cost effectiveness, and reliability. (Author)


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    Title :

    Methods for Approximate Optimum Thrust Programming of Solid Propellant Rockets for Spacecraft Applications


    Contributors:

    Publication date :

    1975


    Size :

    244 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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