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)
Hybrid Electric Chemical Propulsion
1989
27 pages
Report
Keine Angabe
Englisch
Electric & Ion Propulsion , Manned Spacecraft , Electric propulsion , Hybrid propulsion , Space propulsion , Auxiliary , Chemical reactions , Chemicals , Computations , Electricity , Energy , Flow , Fuels , Missions , Models , Oxidizers , Performance(Engineering) , Propellants , Propulsion systems , Ratios , Spacecraft , Thermodynamics , Thrusters
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