Axial force imparted by a conical radiofrequency magneto-plasma thruster

Charles, Christine; Takahashi, Kazunori; Boswell, Roderick

doi:10.1063/1.3694281

Cited by 33 publications

(29 citation statements)

References 11 publications

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“…[12][13][14][15] Here, a magnetized plasma expansion is generated for two gases of separate mass (xenon and argon) in a conical helicon thruster to carry out direct measurement of fuel efficiency. Experiments are performed in a previously described system 16 consisting of a 19.5 cm-long conical helicon plasma thruster (with an inner radius varying from r end ¼ 1.8 cm to r exit ¼ 4.5 cm) attached to a grounded thrust balance 17 and immersed in the 1 meter-diam. 1.4 m-long Irukandji vacuum vessel 18 (equipped with a movable 4 mm diameter disc Langmuir probe), which is pumped down to a base pressure of about 10 À6 Torr.…”

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Boltzmann expansion in a radiofrequency conical helicon thruster operating in xenon and argon

Charles

Boswell

Takahashi

2013

Applied Physics Letters

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Articles you may be interested inDirect measurement of neutral gas heating in a radio-frequency electrothermal plasma micro-thruster Appl. Phys. Lett. 103, 074101 (2013); 10.1063/1.4818657Radiofrequency antenna for suppression of parasitic discharges in a helicon plasma thruster experiment Rev. Sci. Instrum. 83, 083508 (2012); 10.1063/1.4748271Direct thrust measurement of a permanent magnet helicon double layer thruster A low pressure ($0.5 mTorr in xenon and $1 mTorr in argon) Boltzmann expansion is experimentally observed on axis within a magnetized (60 to 180 G) radiofrequency (13.56 MHz) conical helicon thruster for input powers up to 900 W using plasma parameters measured with a Langmuir probe. The axial forces, respectively, resulting from the electron and magnetic field pressures are directly measured using a thrust balance for constant maximum plasma pressure and show a higher fuel efficiency for argon compared to xenon. V C 2013 AIP Publishing LLC.

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“…For zero current in the source solenoid and a current of 6 A in the exhaust solenoid, a maximum magnetic field of about 180 G (0.018 T) is generated. 16 Two distinct thrust balance configurations are used as described in Refs. 12 and 16 to obtain the total generated axial force T total and the axial force T B from the magnetic nozzle.…”

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Boltzmann expansion in a radiofrequency conical helicon thruster operating in xenon and argon

Charles

Boswell

Takahashi

2013

Applied Physics Letters

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“…These studies reported that the detail plasmadynamics and the thrust production mechanism by the magnetic nozzle. Takahashi et al separately measured the electromagnetic thrust force (F diamag ) and the thermal thrust force (F thermal ) produced by the magnetic nozzle, and confirmed the magnetic nozzle theory [12][13][14][15] . The previous researches indicated that the plasma pressure (electron pressure) has to be increased for higher thrust force, and higher magnetic field is needed to confine higher plasma pressure.…”

Section: Introductionmentioning

confidence: 73%

Thrust Performance of High Magnetic Field Permanent Magnet Type Helicon Plasma Thruster

Nakamura¹,

Ito²,

Nishida³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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In order to realize long-lived electric propulsion systems, we have been investigating an electrodeless plasma thruster. In our concept, high-density helicon plasma is accelerated by a magnetic nozzle for thrust production. In order to improve the thrust performance with simple systems, high magnetic flux density magnetic nozzle formed by permanent magnets is employed to our laboratory model plasma thruster. A magnetic circuit, which has high magnetic flux density up to 0.2 T at the magnetic nozzle throat, is constructed by permanent magnets and magnetic yoke. In order to investigate the thrust performance of this thruster, the thrust force is measured by a torsion-pendulum type thrust stand. From the thrust measurement, the thrust force and specific impulse increases with the RF power input. The thrust efficiency is drastically improved by increasing the RF power input, and it is considered to be caused by the discharge mode transition from the CCP to the ICP . The maximum thrust force and thrust efficiency of 2.7 ± 0.4 mN and 0.26 % is measured when the Ar gas mas flow rate is 1.2 mg/s, and plasma production frequency and power is 13.56 MHz and 1000 W. NomenclatureA e = area of thruster exit F diamag = electromagnetic thrust force F thermal = pressure force F total = total thrust force g 0 = acceleration of gravity I sp = specific impulse k B = Boltzmann constant m n = mass of neutral particle m & = injected mass flow rate 2 eff m & = effective mass flow rate ing m & = ingested mass flow rate P c = pressure of vacuum chamber P source = RF power for plasma production T n = temperature of neutral gas (assumed to be 300 K) ∆t = pulse width δ = displacement η = thrust efficiency

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“…This basic electromagnetic thrust force is lower than the other helicon plasma sources [12][13][14][15]24) . The dimensions of our helicon plasma source are smaller diameter and longer length than the other helicon plasma sources.…”

Section: Resultsmentioning

confidence: 99%

“…These studies report that the detail plasmadynamics and the thrust production mechanism by the magnetic nozzle. Takahashi et al separately measured the electromagnetic thrust force and the thermal thrust force produced by the magnetic nozzle, and confirmed the magnetic nozzle theory [12][13][14][15] . The previous researches indicated that the plasma pressure (electron pressure) has to be increased for higher thrust force, and stronger magnetic field is needed to confine higher plasma pressure.…”

Section: Introductionmentioning

confidence: 80%

Preliminary Investigation of Electromagnetic Thrust Characteristics in Electrodeless Compact Helicon Plasma Thruster

Nakamura

Nishida

Shinohara

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

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In order to realize long-lived electric propulsion systems, we have been investigating an electrodeless plasma thruster. In our concept, high-density plasma from a compact helicon plasma source is accelerated by a magnetic nozzle for the thrust production. In order to optimize the thruster design, investigation of the thrust characteristics is needed. In this study, development of the electromagnetic thrust measurement system for compact helicon plasma thrusters and preliminary experiment of thrust measurement have been conducted. We have successfully developed a torsion-pendulum type thrust stand with measurement resolution of 10 N. From the thrust measurement, the electromagnetic thrust increases with the Ar gas mass flow rate and plasma production power. The thrust force and the electron density jump are observed due to the discharge mode transition from the inductively coupled plasma to the helicon wave excited plasma. The electromagnetic thrust force is up to 340 N (Ar gas mass flow rate of 1.0 mg/s, plasma production power of 400 W).

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Axial force imparted by a conical radiofrequency magneto-plasma thruster

Cited by 33 publications

References 11 publications

Boltzmann expansion in a radiofrequency conical helicon thruster operating in xenon and argon

Boltzmann expansion in a radiofrequency conical helicon thruster operating in xenon and argon

Thrust Performance of High Magnetic Field Permanent Magnet Type Helicon Plasma Thruster

Preliminary Investigation of Electromagnetic Thrust Characteristics in Electrodeless Compact Helicon Plasma Thruster

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