Abstract
The thrust performance of a steady-state, applied-field magnetoplasmadynamics (MPD) thruster has been improved by increasing a discharge current was increased from 20 A to 60 A using a lanthanum hexaboride (LaB 6) hollow cathode. The experimentally obtained thrust characteristics were consistent with that of electromagnetic acceleration. Using argon as the propellant, a thrust efficiency of 25.5% and a thrust/power ratio of 17.0 mN/kW were obtained with an applied magnetic field of 265 mT, discharge current of 30 A, propellant mass flow rate of 2.1 mg/s and discharge voltage was 121 V.
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CITATION STYLE
KASUGA, H., JEONG, J., MIZUTANI, K., IWAKAWA, A., SASOH, A., KOJIMA, K., … YASUI, M. (2018). Operation Characteristics of Applied-Field Magnetoplasmadynamics Thruster Using Hollow Cathode. TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 16(1), 69–74. https://doi.org/10.2322/tastj.16.69
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