In this paper, a multiphysics numerical approach for predicting the ionization level in solid rocket engine plumes is presented. Ionization takes place in the rocket combustion chamber and in the exhaust plume. A low-temperature, high-density plasma is created, with small Debye length in most of the plume region. Ambipolar diffusion is therefore assumed for ions and electrons in the plume, and a set of conservation equations is derived to be solved by the numerical model. A number of numerical strategies to resolve this system is derived, as well as a novel scheme that enforces charge neutrality. This approach is integrated into a complex code for compressible, multispecies, turbulent flow simulations. The model is then coupled with a Maxwell’s equations solver in order to simulate the radar cross section of rocket plumes. Finally, computations of ionization levels and radar cross section of a Black Brant rocket plume are presented.


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    Titel :

    Numerical Simulation of Ionized Rocket Plumes


    Beteiligte:
    Gueyffier, D. (Autor:in) / Fromentin-Denoziere, B. (Autor:in) / Simon, J. (Autor:in) / Merlen, A. (Autor:in) / Giovangigli, V. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.04.2014




    Medientyp :

    Aufsatz (Konferenz) , Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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