Statement and mathematical formulation of extremum problem associated with optimum design of spacecraft impact limiters (payload plus energy dissipator) are presented; semigeometric solution is given; it is shown that, in general, practical rather than true maximum for objective function, developed as payload fraction, exists in solution domain; energy dissipators having high specific energy capacities (energy dissipated per pound of material) are best suited for achieving optimum system design. (11875)


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    Title :

    Materials-design synthesis for optimum design of spacecraft energy-dissipating systems


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Journal of Spacecraft and Rockets ; 5 , n 10 ; p 1170-1174


    Publication date :

    1968


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :