Abstract
Abstract : 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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