Multiprobe characterization of plasma flows for space propulsion

Damba, J.; Argente, P.; Cervone, Angelo; Domenech-Garret, J. L.; Conde, Luis

doi:10.1088/1742-6596/958/1/012002

Cited by 9 publications

(6 citation statements)

References 14 publications

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“…This explains the lack of response of the low ion group in Fig. 7.5 to throttle voltage and its distribution as an uniform background in the steady state [15][16][17]. A similar response can be expected for the multi-electrode structures of Figs.…”

Section: The Mesothermal Plasma Flowsupporting

confidence: 75%

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Plasma Thrusters for In-Space Propulsion; New Trends and Physical Limitations

Dyubo

González

Tsybin

et al. 2020

Springer Proceedings in Physics

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In-space plasma propulsion is today a necessity for the economic competitiveness of commercial satellites. In plasma thrusters the impulse is imparted by a mesothermal plasma jet where ions drift a supersonic velocities. Compact multielectrode systems for ion acceleration are studied by a combination of analytical calculations and computer simulations. The results show exahust speeds of 140 km/s can be reached with specific impulses higher than unsual plasma thrusters. Additionally, the ion velocity distribution functions of the plasma jet exhasut obtained with retarded field energy analyzers that can be used to cross validate the results of numerical simulations.

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Section: The Mesothermal Plasma Flowsupporting

confidence: 75%

“…parallel to the RFEA axis of symmetry was about ±8 eV for singly charged Argon ions of 400 eV energy. This is equivalent to radial speeds of ±6 km/s for ions with axial velocities of 44 km/s [15].…”

Section: The Mesothermal Plasma Flowmentioning

confidence: 99%

Plasma Thrusters for In-Space Propulsion; New Trends and Physical Limitations

Dyubo

González

Tsybin

et al. 2020

Springer Proceedings in Physics

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“…As we shall see, the response of this system has been tested under low neutral gas pressures and also under realistic ambient plasma conditions using the Alternative Low Power Hybrid Ion Engine (ALPHIE) plasma thruster. [12][13][14][15] The characteristics of the thrust stand are discussed in Sec. II and its calibration tests and performance are in Sec.…”

Section: Articlementioning

confidence: 99%

“…The thrust stand was used to determine the impulses delivered by our ALPHIE plasma engine whose performances and operation have been previously discussed. [12][13][14][15] Briefly, when the propellant neutral gas valve is open, a stationary mass flow rate Q of argon or xenon gas is introduced into the plasma chamber of the thruster and the ion acceleration potential VAC between 450 V and 750 V is fixed. The typical thruster currents IE in the tests were in the range of 200-400 mA and the total electric power consumption of 200-325 W. 12 The only cathode is disposed in front of its two-grid acceleration system.…”

Section: The Thrust Measurement Processmentioning

confidence: 99%

Thrust stand based on a single point load cell for impulse measurements from plasma thrusters

Conde

Lahoz

Grabulosa

et al. 2020

Review of Scientific Instruments

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We introduce a simple thrust stand for the direct measurement of the millinewton impulses or thrusts delivered by small thrusters intended for in-space electric propulsion. The thruster under test, with a weight below 1.5 kg, is disposed on a horizontal platform and its impulse is measured as an overweight by using a strain gauge cell physically protected from the ambient plasma and vacuum conditions. This system provides ten thrust readings per second with noise peak to peak amplitudes of 0.10-0.18 mN. The calibration procedures to verify its dynamic response to time dependent thrusts in the range of 0-15 mN using control weights as well as its minimum thrust sensitivity δTs = 0.3 mN are discussed. Additionally, its simple conception permits a plain data reduction and analysis of steady state and low frequency thrust transients. This thrust stand was employed under low pressure and plasma ambient conditions to measure the steady impulses delivered by the Alternative Low Power Hybrid Ion Engine (ALPHIE) of 0.4-4.0 mN with absolute errors T = ±0.3 mN. Finally, the experimental results show that a control electric voltage governs the ALPHIE thruster throttle.

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“…Since measurement noise amplification is inherent to the differentiation process, filtering/fitting methods may be necessary to smooth the measured I-V data without causing significant distortion and to obtain accurate first and second derivatives. Among the numerical methods, the Savitzky-Golay filter is one of the most commonly employed for IEDF/EEDF derivations [21][22][23][24][25] . Fernández Palop et al 26 implemented a Gaussian filter to smooth the I-V characteristics and evaluate the electron-energy distribution function.…”

Section: Introductionmentioning

confidence: 99%

Data Processing Techniques for Ion and Electron Energy Distribution Functions

Caldarelli¹,

Filleul²,

Boswell³

et al. 2022

Preprint

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Retarding field energy analyzers and Langmuir probes are routinely used to obtain ion and electron energy distribution functions (IEDF, EEDF). These typically require knowledge of the first and second derivatives of the I-V characteristics, both of which can be obtained in various ways. This poses challenges inherent to differentiating noisy signals, a frequent problem with electric-probe plasma diagnostics. A brief review of commonly used analog and numerical filtering and differentiation techniques is presented, together with their application on experimental data collected in a radio-frequency plasma. The application of each method is detailed with regards to the obtained IEDF and EEDF, the deduced plasma parameters, dynamic range, energy resolution and signal distortion.

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Multiprobe characterization of plasma flows for space propulsion

Cited by 9 publications

References 14 publications

Plasma Thrusters for In-Space Propulsion; New Trends and Physical Limitations

Plasma Thrusters for In-Space Propulsion; New Trends and Physical Limitations

Thrust stand based on a single point load cell for impulse measurements from plasma thrusters

Data Processing Techniques for Ion and Electron Energy Distribution Functions

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