A spacecraft propulsion concept that uses a combination of electrical energy and chemical energy for thrust is explored using thermodynamic modeling calculations. The essence of this concept consists of adding a carefully chosen amount of O2 or F2 oxidizer to the propellant flow of a conventional H2 electrothermal thruster. A general method is given for selecting the Fuel: oxidizer ratio so as to optimize the thruster performance for any set of mission constraints. Auxiliary propulsion, Chemically augmented electrothermal thrusters, Electric propulsion, Spacecraft propulsion. (mjm)


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    Titel :

    Hybrid Electric Chemical Propulsion


    Beteiligte:
    J. E. Pollard (Autor:in) / R. B. Cohen (Autor:in)

    Erscheinungsdatum :

    1989


    Format / Umfang :

    27 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Hybrid electric chemical propulsion

    POLLARD, J. / COHEN, R. | AIAA | 1985


    Hybrid electric chemical propulsion

    POLLARD, J. E. / COHEN, R. B. | AIAA | 1986



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