Two metallized solid rocket propellant formulations, based on either the standard AP/HTPB matrix commonly used in space propulsion or the new matrix ADN/GAP, were analyzed. The two formulations in terms of ideal thermochemistry and experimental combustion properties were compared. Thus, a dual-oxidizer system bound by an active binder and loaded with a dual metal fuel was proposed as optimum formulation for space exploration missions. For all configurations, only laboratory level testing was discussed. For motor applications, full-scale testing is needed to ensure a complete mastering of the process.


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    Title :

    New energetic ingredients for solid rocket propulsion


    Contributors:
    DeLuca, L.T. (author) / Palmucci, I. (author) / Franzin, A. (author) / Weiser, V. (author) / Gettwert, V. (author) / Wingborg, N. (author) / Sjoblom, M. (author)


    Publication date :

    2016


    Size :

    10 pages


    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    Unknown




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