HCEP Phase I STTR Principal Investigator Christopher Davis PhD ElectroDynamic Applications Inc Ann Arbor Michigan University Principal Investigator Professor Michael Micci Penn State University ID: 784096
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Hybrid Chemical-Electric Propulsion(HCEP)
Phase I STTRPrincipal Investigator: Christopher Davis, PhDElectroDynamic Applications, Inc.Ann Arbor, MichiganUniversity Principal Investigator: Professor Michael MicciPenn State UniversitySpace Power and Propulsion Program Review, September 12th, 2012
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Slide2HCEP Thruster Concept
2Can be operated as a chemical thruster and a low or high Isp electric thruster using same ionic liquid (IL) propellantChemical, high thrust mode – Ignite and bring to complete combustion using microwaves in central chamberLow electric Isp mode – Electrothermal heating of combustion products to ~ double Isp (<1000 s)Estimated 3-N thrust with 25 kW, 50% thruster efficiencyHigh electric Isp mode – microwave energy used to ionize IL propellant; ions then accelerated electrostaticallyEstimated Isp of ~3000 s
Slide3Phase I Tasks (1 of 2)
3Characterization of IL (ionic liquid) ignition and sustainability Measure microwave ignition as a function of flow rate and powerTesting performed at PSU facilities using available AF-315EDemonstration of microwave electrothermal heating of representative combustion productsCharacterization of mixtures of CO2, H2O, N2, N2O, etc.
Slide4Phase 1 Tasks (2 of 2)
4Validation of electrostatic acceleration of simulated ionic liquid components Run well-characterized Hall thruster using representative IL components (CO2, N2O, H2O, and N2 )Compare results to Xenon performanceTesting performed at University of Michigan’s Plasmadynamics and Electric Propulsion Laboratory (PEPL) Large Vacuum Test Facility (LVTF)Development of conceptual design of a HCEP thruster
Electrostatic acceleration design
Neutralizer design and integration
Method for switching of microwave power between igniter or ionizer
Thruster design to operate in 30 kW power range