Space Simulation Testing of the Helicon Double Layer Thruster Prototype

West, Michael; Charles, Christine; Boswell, Rod

doi:10.2514/6.2010-7016

Cited by 5 publications

(1 citation statement)

References 152 publications

(257 reference statements)

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“…Combination of a helicon plasma production and magnetoplasma dynamics acceleration which is powered by radio frequency waves could be a solution because of no physical contact between the plasma and electrodes (electrodeless). Various schemes have been under development to realize electrodeless electric propulsion: VASIMR, 2 HDLT, [3][4][5][6][7] and others. [8][9][10][11] We have been studying one of the electrodeless thruster, which is called Lissajous acceleration method, [12][13][14][15][16][17][18][19] whose concept is shown in Fig.…”

Section: Introductionmentioning

confidence: 99%

Laboratory Model Development of Lissajous Acceleration for Electrodeless Helicon Plasma Thruster

Matsuoka

Funaki

Satoh

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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A thrust model for a Lissajous method has shown that a competitive performance compared with the rockets using, e.g., ion engines or Hall thrusters, can be achieved by electrodeless method which can be a long lived thruster. Previous experiments showed a slight increase of plasma flow velocity by this method, however, experimental conditions were not optimized and the thrust was not measured. In this study, two experiments are reported in order to develop helicon plasma sources and a thrust measurement method by using Ar gas propellant. The first experiment is measurements of thermal thrust in order to characterize thruster performance 26 mm and 50 mm diameter helicon plasma thrusters without Lissajous acceleration. Maximum specific impulse (390 ± 130 s) is observed at a parameter set: the mass flow rate of 0.24 mg/s, the magnetic field: B Z = 0.054 T and RF (radio frequency) input power of 2.0 kW when a 50 mm diameter thruster is used. It is found that the thrust and efficiency is proportional to absorbed power by the plasma. The second experiment is preliminary measurements of Lissajous acceleration by using a laboratory model of 50 mm diameter. Preliminary thrust measurements by using the laboratory model show clear plasma acceleration by applying acceleration power. The observed thrust with acceleration power of 130 W is 3.3±0.3 mN with a specific impulse of 380±40 s and efficiency 2 of 0.40 ±0.08 %. When acceleration power is turned off, the observed thrust is 2.9±0.3 mN with a specific impulse of 330±40 s and efficiency of 0.39 ±0.09 %. The improvement of thruster performance by applying acceleration power is achieved at a non-optimized condition and a small fraction (7 %) of the RF power available for the acceleration. NomenclatureB z = Axial magnetic field c s = Ion sound velocity HDLT = Helicon Double Layer Thruster PM-HDLT= Permanent Magnet HDLT HEAT = Helicon Electrodeless Advanced Thrusters I = r.m.s. RF current I.D. = Inner Diameter LHPD = Large Helicon Plasma Device M = Ion mass P in = RF input power P abs = Absorbed RF power by plasma RF = Radio frequency T e = Electron temperature VASIMR = Variable Specific Impulse Magnetoplasma Rocket Z = Impedance  = Boltzmann constant

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