Momentum flux measuring instrument for neutral and charged particle flows

Chavers, D. G.; Chang‐Diaz, Franklin

doi:10.1063/1.1505107

Cited by 62 publications

(45 citation statements)

References 1 publication

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“…4 and Table 1 also include corrections for sputtering based on SRIM/TRIM models 12 (see Section IV A for further sputtering correction details). The increase in thruster force with reduced thrustertarget separation distance was previously observed by Chavers et al 1 in a similar experiment (see Section D), and is attributed to an increased neutral pressure near the HET exit plane. Due to finite facility pressure, background neutrals continually reach the thruster discharge channel, become ionized, accelerated, and artificially increase thrust.…”

Section: A Thruster-sensor Separation Distancesupporting

confidence: 62%

“…Calibration was performed in the same manner as was previously described by Chavers et al 1 , in which a set of calibrated weights were hung from a tethered string assembly to apply a known tension force on the graphite target disc. Figure 3 shows a representative example of the force-to-voltage relation for the particular device used in this experiment campaign.…”

Section: E Calibrationmentioning

confidence: 99%

“…1 The PMFS was placed in the flowing plasma stream of the P5 HET where real time force measurements were made with both the PMFS and the thrust stand. The PMFS was able to measure the force exerted on it with a resolution of 0.1 mN, and an average discrepancy of 2% compared to the thrust stand.…”

Section: Introductionmentioning

confidence: 99%

“…Instead, a simple, robust, and low-cost plasma impact force sensor can be used to reliably determine the total force produced by an electric propulsion thruster. Until now, only a handful [1][2][3][4][5] of experiments focused on impact force sensors. Virtually no experiments have attempted to compare the accuracy of an impact thrust sensor to the more commonly used inverted pendulum thrust stand.…”

Section: Introductionmentioning

confidence: 99%

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Hall Thruster and VASIMR VX-100 Force measurements using a Plasma Momentum Flux Sensor

Longmier

Bering

Reid

et al. 2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The accuracy of a plasma impact force sensor was compared to that of the more commonly used inverted pendulum thrust stand using a 5 kW Xe Hall effect thruster (HET). An improved plasma momentum flux sensor (PMFS) was designed and constructed based on a previous design. Real-time force measurements were made with both the PMFS and the inverted pendulum thrust stand. The PMFS measured the force exerted onto it from the HET exhaust plume with a resolution of 0.1 mN, and an average discrepancy of 2% compared to thrust stand measurements. Experiments were completed using a 9 m by 6 m cylindrical vacuum chamber. The total force from the HET was modulated from 34 mN to 356 mN by varying both the anode voltage, from 150 V to 500 V, and the neutral Xe gas flow rate from 5 mg/s to 15 mg/s. Initial force measurements from the Variable Specific Impulse Magnetoplasma Rocket (VASIMR) VX-100 are analyzed and compared to RPA data.

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Section: A Thruster-sensor Separation Distancesupporting

confidence: 62%

Section: E Calibrationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Hall Thruster and VASIMR VX-100 Force measurements using a Plasma Momentum Flux Sensor

Longmier

Bering

Reid

et al. 2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…Methods such as the Ion Cyclotron Range Heating (ICRH), Lower Hybrid (LH) wave heating, and the current drive have been suggested for ion heating in fusion devices [30,31,32]. The ICRH scheme is also employed in the VASIMR experimental rocket concept [33,34,35]. In addition, ion heating by various electromagnetic and electrostatic instabilities has been observed in the Earth ionosphere [36,37,38,39,40].…”

Section: Introductionmentioning

confidence: 99%

Coherent Ion Acceleration Using Beating Electrostatic Waves

Choueiri¹

2004

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118REPORT DOCUMENTATION PAGE R 05-The public reporting burden for this collection of information is estimated tol rage 1 hour per response, including the tim gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regar of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters S, (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that r subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control n PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)2. REPORT TYPE 3. DATES COVERED (From -To) SPONSOR/MONITOR'S REPORT NUMBER(S)12. DISTRIBUTION/AVAILABILITY STATEMENT Distribution Statement A. Approved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTThe results obtained from AFOSR-sponsored study on a new ion acceleration using beating electrostatic waves. Unlike previously known methods of energizing plasmas with electrostatic waves, and which accelerate only ions whose initial velocities are above a certain threshold (close to the waves velocity), the new mechanism can accelerate ions with arbitrarily small initial velocities. This results in significant improvements to the acceleration/heating efficiency (by as much as 45%) over previous techniques. The benefits to the state of the art of space propulsion stem from the high efficiency of the new mechanism,its thersholdless nature and its capabilities of producing high ion energies and its electrodeless character. In summary project accomplished the following: 1 Demonstrated theoretically that a new highly efficient ion acceleration mechanism by heating electrostatic (ES) waves is teal and ii a fundamental phenomenon that occurs only under specific conditions. 2. Studied using Monte Carlo simulations the effects of collisions (that would occur in a real low temperature plasma) on the ion acceleration mechanism and found that collisions can enhance the effects due to scattering of ions out of the forbidden region of phase space. 3. Designed and constructed a dedicated experiment to study the new ion acceleration mechanism. SUBJECT TERMS SECURITY CLASSIFICATION SYNOPSISIn this final technical report we document, in three chapters, the results obtained from our AFOSR-sponsored study on a new ion acceleration using beating electrostatic waves.Unlike previously known methods of energizing plasmas with electrostatic waves, and which accelerate only ions whose initial velocities are above a certain threshold (close to the waves velocity), the new mechanism can accelerate ions with arbitrarily small initial velocities (as illustrated in Fig. (1)). This results in significant improvements to the acceleration/heating efficiency (by as much as 45%) over previous techniques. The benefits to the state of the art of space propulsion stem from the high efficiency of the new mechanis...

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