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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    Title :

    Hybrid Electric Chemical Propulsion


    Contributors:
    J. E. Pollard (author) / R. B. Cohen (author)

    Publication date :

    1989


    Size :

    27 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    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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