<i>Basic Data of Plasma Physics, 1966 (2nd revised edition)</i>

Brown, Sanborn C.; Malamud, Herbert

doi:10.1063/1.3034897

Cited by 24 publications

(38 citation statements)

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“…Argon propellant is introduced via the center hole of the back plate using a 1 mminner diameter and 2 mm-outer diameter ceramic tube. In the present experiments the argon flow rate is maintained at 25 sccm (0.75 mg s −1 ) using a mass flow controller with an uncertainty of ±1% in the flow rate; the chamber pressure measured by a baratron gauge connected to a side port of the chamber was 0.8 mTorr and the electron-neutral collision mean free path is roughly estimated as ∼65 cm assuming a collisional cross-section of ∼6 × 10 −20 m −2 [28]. A 10 cminner diameter, 16.4 cm-outer diameter and 5 cm wide solenoid with 560 turns is centered at z = −3.4 cm to create a magnetic nozzle using a solenoid current of up to I B = 15 A.…”

Section: Methodsmentioning

confidence: 99%

Effect of magnetic and physical nozzles on plasma thruster performance

Takahashi

Charles

Boswell

et al. 2014

Plasma Sources Sci. Technol.

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Plasma cross-field diffusion in a magnetic nozzle is inhibited by increasing the magnetic field strength in a helicon plasma thruster attached to a pendulum thrust balance, while maintaining constant plasma density and electron temperature in the source tube, i.e. a constant plasma injection into the magnetic nozzle, where the field strength near the radio frequency (rf) antenna is less than 210 G and the operating argon pressure in the vacuum chamber is 0.8 mTorr. Inhibition of the cross-field diffusion yields a higher electron pressure in the magnetic nozzle and a resultant larger thrust. The thrust component arising from the magnetic nozzle approaches the theoretical limit derived from an ideal magnetic nozzle approximation where no plasma is lost from the nozzle and there is an azimuthal plasma current originating from the electron diamagnetic drift. It is also shown that the momentum of the plasma lost from the magnetic nozzle is captured by a physical nozzle attached at the source exit resulting in a larger thrust. Two physical nozzles of different sizes (nozzle 1: 10.5 cm in length with a maximum diameter of 20 cm, nozzle 2: 26 cm in length with a maximum diameter of 36 cm) are tested. The maximum thrust of 20 ± 1 mN is obtained for 25 sccm argon propellant and 2 kW rf power with a reflection power less than 5 W, which gives a specific impulse of 2750 ± 165 s and a thrust efficiency of 13.5 ± 1.5%.

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Section: Methodsmentioning

confidence: 99%

Effect of magnetic and physical nozzles on plasma thruster performance

Takahashi

Charles

Boswell

et al. 2014

Plasma Sources Sci. Technol.

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“…A (kPa −1 cm −1 ) C γ i (E kin range) d (µm) Gas Literature [28] Experiment (RF) γ Literature [31] a γ calculated from literature data [28].…”

Section: Table 2 Estimated Experimental Secondary Electron Emission C...mentioning

confidence: 99%

High frequency glow discharges at atmospheric pressure with micro-structured electrode arrays

Baars-Hibbe¹,

Sichler²,

Schrader³

et al. 2005

J. Phys. D: Appl. Phys.

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Micro-structured electrode (MSE) arrays allow the generation of large-area uniform glow discharges over a wide pressure range up to atmospheric pressure. The electrode widths, thicknesses and distances in the micrometre range are realized by means of modern micro-machining and galvanic techniques. The electrode distance, the gap width d, is small enough to generate sufficiently high electric field strengths to ignite gas discharges by applying only moderate radio frequency (RF, 13.56 MHz) voltages (80-390 V in Ne, He, Ar, N 2 and air). The non-thermal plasma system is characterized by a special probe measuring the electric parameters. We tested MSE arrays with d = 70, 25 and 15 µm. The MSE driven plasmas show a different behaviour from conventional RF discharge plasmas. Due to the very small electrode gap width we can describe the behaviour of the charged particles in the RF field of our system with the dc Townsend breakdown theory, depending on the pressure range and gas. With decreasing pressure, the gas discharges, especially in Ne and He, are increasingly dominated by field electron emission. With the MSE arrays as plasma sources several applications were developed and successfully tested, e.g. decomposition of waste gases and sterilization of food packaging materials at atmospheric pressure.

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“…Here, c tr and d tr are coefficients describing the electronatom transport scattering cross section, extracted from Brown (1966). The accuracy of Eq.…”

Section: Simple Model For Bubble Opacitymentioning

confidence: 99%

Single Bubble Sonoluminescence

Arakeri¹

2004

Sonoluminescence

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Single-bubble sonoluminescence occurs when an acoustically trapped and periodically driven gas bubble collapses so strongly that the energy focusing at collapse leads to light emission. Detailed experiments have demonstrated the unique properties of this system: the spectrum of the emitted light tends to peak in the ultraviolet and depends strongly on the type of gas dissolved in the liquid; small amounts of trace noble gases or other impurities can dramatically change the amount of light emission, which is also affected by small changes in other operating parameters (mainly forcing pressure, dissolved gas concentration, and liquid temperature). This article reviews experimental and theoretical efforts to understand this phenomenon. The currently available information favors a description of sonoluminescence caused by adiabatic heating of the bubble at collapse, leading to partial ionization of the gas inside the bubble and to thermal emission such as bremsstrahlung. After a brief historical review, the authors survey the major areas of research: Section II describes the classical theory of bubble dynamics, as developed by Rayleigh, Plesset, Prosperetti, and others, while Sec. III describes research on the gas dynamics inside the bubble. Shock waves inside the bubble do not seem to play a prominent role in the process. Section IV discusses the hydrodynamic and chemical stability of the bubble. Stable single-bubble sonoluminescence requires that the bubble be shape stable and diffusively stable, and, together with an energy focusing condition, this fixes the parameter space where light emission occurs. Section V describes experiments and models addressing the origin of the light emission. The final section presents an overview of what is known, and outlines some directions for future research.

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Basic Data of Plasma Physics, 1966 (2nd revised edition)

Cited by 24 publications

References 0 publications

Effect of magnetic and physical nozzles on plasma thruster performance

Effect of magnetic and physical nozzles on plasma thruster performance

High frequency glow discharges at atmospheric pressure with micro-structured electrode arrays

Single Bubble Sonoluminescence

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