Emission Characteristics of Passively Fed Electrospray Microthrusters with Propellant Reservoirs
| Autor: | Paulo C. Lozano, Robert E. Thomas, David Krejci, Thomas W. Haag, Fernando Mier-Hicks |
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| Přispěvatelé: | Massachusetts Institute of Technology. Department of Aeronautics and Astronautics, Krejci, David, Mier Hicks, Fernando, Lozano, Paulo C |
| Rok vydání: | 2017 |
| Předmět: |
010302 applied physics
Microelectromechanical systems Propellant Electrospray Materials science Ion thruster business.industry Electrical engineering Aerospace Engineering 02 engineering and technology 021001 nanoscience & nanotechnology 01 natural sciences Cold gas thruster Physics::Plasma Physics Space and Planetary Science Physics::Space Physics 0103 physical sciences Physics::Accelerator Physics Optoelectronics Pulsed inductive thruster Colloid thruster 0210 nano-technology business Common emitter |
| Zdroj: | Krejci |
| ISSN: | 1533-6794 0022-4650 |
| Popis: | The characterization of a miniaturized ionic liquid electrospray thruster for nanosatellite applications is presented. The thruster investigated features an emitter array of 480 emitter tips per square centimeter and a 1 cm[superscript 3] propellant tank with an entirely passive propellant supply; it is operated at a power level of less than 0.15 W. The paper presents energy- and mass-resolving beam spectroscopy of the packaged thruster system, as well as two independent thrust measurements. This allows derivation of thruster performance parameters under realistic firing conditions, including individual thruster efficiency contributions, specific impulse, and thrust. The total thruster efficiencies of 36%; specific impulse of ∼760 s, including all losses; and thrust of 11–12.5 μN are presented at emission currents of 150 μA for a device of ∼1 cm[superscript 2]. The current emission data without current decay of ∼90 h are presented with a maximum of 172 h. United States. National Aeronautics and Space Administration (Contract NNL13AA12C) |
| Databáze: | OpenAIRE |
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