Compact vacuum arc micro-thruster for small satellite systems

Qi, N.; Schein, J.; Binder, Róbert; Krishnan, M.; Anders, André; Polk, Jay

doi:10.2514/6.2001-3793

Cited by 9 publications

(5 citation statements)

References 9 publications

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“…For these reasons a vacuum arc source was developed and used for an ion thruster [27]. This work led to development of a co-axial vacuum arc plasma thruster [28]. Schematically this thruster is shown in figure 2.…”

Section: Micro-vacuum Arc Thrustermentioning

confidence: 99%

Electric propulsion for small satellites

Keidar¹,

Zhuang²,

Shashurin³

et al. 2014

Plasma Phys. Control. Fusion

142

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Propulsion is required for satellite motion in outer space. The displacement of a satellite in space, orbit transfer and its attitude control are the task of space propulsion, which is carried out by rocket engines. Electric propulsion uses electric energy to energize or accelerate the propellant. The electric propulsion, which uses electrical energy to accelerate propellant in the form of plasma, is known as plasma propulsion. Plasma propulsion utilizes the electric energy to first, ionize the propellant and then, deliver energy to the resulting plasma leading to plasma acceleration. Many types of plasma thrusters have been developed over last 50 years. The variety of these devices can be divided into three main categories dependent on the mechanism of acceleration: (i) electrothermal, (ii) electrostatic and (iii) electromagnetic. Recent trends in space exploration associate with the paradigm shift towards small and efficient satellites, or micro-and nano-satellites. A particular example of microthruster considered in this paper is the micro-cathode arc thruster (µCAT). The µCAT is based on vacuum arc discharge. Thrust is produced when the arc discharge erodes some of the cathode at high velocity and is accelerated out the nozzle by a Lorentz force. The thrust amount is controlled by varying the frequency of pulses with demonstrated range to date of 1-50 Hz producing thrust ranging from 1 µN to 0.05 mN.

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Section: Micro-vacuum Arc Thrustermentioning

confidence: 99%

Electric propulsion for small satellites

Keidar¹,

Zhuang²,

Shashurin³

et al. 2014

Plasma Phys. Control. Fusion

142

View full text Add to dashboard Cite

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“…The performance of the VAT is determined by the propellant mass, the degree of ionization of the plasma, the angle of expansion, the average charge state and the ion velocity. All these parameters have been measured repeatedly in the past and verified for numerous materials and operating conditions [5][6][7][8]. Typical values for the ion velocity vary between 10 and 30 km s −1 , the average arc/ion current ratio has been shown to be of the order of 8% and a cosine distribution has been found to emulate the plasma plume expansion very well.…”

Section: Aasc Vacuum Arc Thrustermentioning

confidence: 95%

“…The plasma jet has a free radial boundary whose position will be determined as part of a self-consistent solution. The plasma jet model is based on the following assumptions and conditions: (1) the vacuum arc plasma is fully ionized; (2) during the expansion, the temperature of each species remains constant; (3) the mean free path for elastic electron-ion collisions is much smaller than the characteristic plasma jet radius; (4) the ions and electrons are ideal gases with partial pressures P α = kT α N α , where α = e, i and k is Boltzmann's constant; (5) the electrons are magnetized and the ions are unmagnetized, i.e. ρ i R 0 ρ e , where ρ e , ρ i are the electron and ion Larmor radii, respectively; (2) the plasma is quasi-neutral.…”

Section: The Hydrodynamic Model Of the Vacuum Arc Thrustermentioning

confidence: 99%

“…The measured energy efficiency was about 80% that is comparable to that of the Xenon ion thruster. The development of the vacuum arc source for an ion thruster led to the design of a thruster based on the pulsed vacuum arc without any ion extraction [5]. For latter configuration, a specific impulse of about 1000 s was measured and 21% of efficiency was estimated.…”

Section: Introductionmentioning

confidence: 99%

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Magnetically enhanced vacuum arc thruster

Keidar

Schein

Wilson

et al. 2005

Plasma Sources Sci. Technol.

112

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A hydrodynamic model of the vacuum arc thruster and its plume is described. Primarily an effect of the magnetic field on the plume expansion and plasma generation is considered. Two particular examples are investigated, namely the magnetically enhanced co-axial vacuum arc thruster (MVAT) and the vacuum arc thruster with ring electrodes (RVAT). It is found that the magnetic field significantly decreases the plasma plume radial expansion under typical conditions. Predicted plasma density profiles in the plume of the MVAT are compared with experimental profiles, and generally a good agreement is found. In the case of the RVAT the influence of the magnetic field leads to plasma jet deceleration, which explains the non-monotonic dependence of the ion current density, on an axial magnetic field observed experimentally.

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“…Among the few options that do exist are vacuum arc thrusters (VAT). [1][2][3] These thrusters provide thrust by utilizing the high velocity ions ejected from the cathode of a vacuum arc. The reduced mass of these thrusters is achieved by using an inductive energy storage (IES) power processing unit.…”

Section: Introductionmentioning

confidence: 99%

Macroparticle Charging in a Pulsed Vacuum Arc Thruster Discharge

Rysanek¹,

Burton²,

Keidar³

2006

42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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A pulsed vacuum arc discharge emits a plasma as well as macroparticles in the form of micron-sized molten droplets of cathode material. Due to their trajectory and size, these macroparticles often pose a contamination threat for both spacecraft-based thrusters, and thin film deposition systems. The charge of these macroparticles was experimentally measured, and compared to a model based on thermionic electron emission at T~2500K. The model predicts and the experimental results verify that the charge on the macroparticles is positive, as compared to the negative charge expected for a DC vacuum arc. Experimental results show a roughly quadratic dependence of particle charge on the particle diameter, with a 1 µm diameter particle having a charge of approximately 1000 x 1.6 x 10-19 C. Model results show a roughly quadratic charge dependence for particles smaller than 1.2 µm and a roughly linear dependence for particles greater than 2 µm.

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Compact vacuum arc micro-thruster for small satellite systems

Cited by 9 publications

References 9 publications

Electric propulsion for small satellites

Electric propulsion for small satellites

Magnetically enhanced vacuum arc thruster

Macroparticle Charging in a Pulsed Vacuum Arc Thruster Discharge

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