Validating and optimising mismatch tolerance of Doppler backscattering measurements with the beam model

We use the beam model of Doppler backscattering (DBS), which was previously derived from beam tracing and the reciprocity theorem, to shed light on mismatch attenuation. This attenuation of the backscattered signal occurs when the wavevector of the probe beam's electric field is not in the plane perpendicular to the magnetic field. Correcting for this effect is important for determining the amplitude of the actual density fluctuations. Previous preliminary comparisons between the model and Mega-Ampere Spherical Tokamak (MAST) plasmas were promising. In this work, we quantitatively account for this effect on DIII-D, a conventional tokamak. We compare the predicted and measured mismatch attenuation in various DIII-D, MAST, and MAST-U plasmas, showing that the beam model is applicable in a wide variety of situations. Finally, we performed a preliminary parameter sweep and found that the mismatch tolerance can be improved by optimising the probe beam's width and curvature at launch. This is potentially a design consideration for new DBS systems

Multiprobe characterization of plasma flows for space propulsion

Plasma engines for space propulsion generate plasma jets (also denominated plasma plumes) having supersonic ion groups with typical speeds in the order of tens of kilometers per second, which lies between electron and ion thermal speeds. Studies of the stationary plasma expansion process using a four-grid retarding field energy analyzer (RFEA), an emissive probe (EP) and a Langmuir probe (LP), all mounted on a three dimensionally (3D) displaced multiprobe structure are discussed. Specifically, the determination of plasma beam properties from the RFEA current ?voltage (IV) characteristic curves is presented. The experimental results show the ion energy spectra to be essentially unchanged over 300 mm along the plasma-jet expansion axis of symmetry. The measured ion velocity distribution function (IVDF) results from the superposition of different ion groups and has two dominant populations: A low-energy group constituted of ions from the background plasma is produced by the interaction of the plasma jet with the walls of the vacuum chamber. The fast-ion population is composed of ions from the plasma beam moving at supersonic speeds with respect to the low-energy ions. The decreasing spatial profiles of the plasma-jet current density are compared with those of the low-energy ion group, which are not uniform along the axis of symmetry because of the small contributions from other ion populations with intermediate speeds

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

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 0?15 mN using control weights as well as its minimum thrust sensitivity ?Ts = 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

Multiprobe characterization of plasma flows for space propulsion

Plasma engines for space propulsion generate plasma jets (also denominated plasma plumes) having supersonic ion groups with typical speeds in the order of tens of kilometers per second, which lies between electron and ion thermal speeds. Studies of the stationary plasma expansion process using a four-grid retarding field energy analyzer (RFEA), an emissive probe (EP) and a Langmuir probe (LP), all mounted on a three dimensionally (3D) displaced multiprobe structure are discussed. Specifically, the determination of plasma beam properties from the RFEA current-voltage (IV) characteristic curves is presented. The experimental results show the ion energy spectra to be essentially unchanged over 300 mm along the plasma-jet expansion axis of symmetry. The measured ion velocity distribution function (IVDF) results from the superposition of different ion groups and has two dominant populations: A low-energy group constituted of ions from the background plasma is produced by the interaction of the plasma jet with the walls of the vacuum chamber. The fast-ion population is composed of ions from the plasma beam moving at supersonic speeds with respect to the low-energy ions. The decreasing spatial profiles of the plasma-jet current density are compared with those of the low-energy ion group, which are not uniform along the axis of symmetry because of the small contributions from other ion populations with intermediate speeds.Space Systems Egineerin

Physics and performance of the Alternative Low Power Hybrid Ion Engine (ALPHIE) for space propulsion

The current status and performance of the ALPHIE plasma thruster is discussed. This new concept was the subject of two recently granted patents and is radically different from conventional (Kauffman) gridded ion engines. Since it makes use of three DC power supplies and only one electron-emitting cathode disposed outside the plasma chamber, its power processing unit has low requisites. This electron emission is employed for both ionization and neutralization of the ion beam. Contrary to usual ion engines where only ions flow through the grids, in this case ionizing electrons and supersonic ions counterflow through the open spaces of a two-grid system. The performance of this plasma thruster was determined using both laboratory tests and particle-in-cell numerical simulations which confirmed the basic physical principles of the ion acceleration process. Laboratory experiments under realistic conditions show the ALPHIE thruster to produce supersonic Argon plasma flows with peak speeds of 37-44 km/s and therefore specific impulses in the range 3700-4400 s−1 . Additionally, ALPHIE delivers 1-3.5 mN throtteable thrusts using a maximum 325 W peak power, all of which were directly measured in the laboratory. These performances make ALPHIE suitable for station keeping, flight formation and end-of-life disposal of small and medium sized satellites