L. Garrigues

Space micropropulsion systems for Cubesats and small satellites: From proximate targets to furthermost frontiers

Rapid evolution of miniaturized, automatic, robotized, function-centered devices has redefined space technology, bringing closer the realization of most ambitious interplanetary missions and intense near-Earth space exploration. Small unmanned satellites and probes are now being launched in hundreds at a time, resurrecting a dream of satellite constellations, i.e., wide, all-covering networks of small satellites capable of forming universal multifunctional, intelligent platforms for global communication, navigation, ubiquitous data mining, Earth observation, and many other functions, which was once doomed by the extraordinary cost of such systems. The ingression of novel nanostructured materials provided a solid base that enabled the advancement of these affordable systems in aspects of power, instrumentation, and communication. However, absence of efficient and reliable thrust systems with the capacity to support precise maneuvering of small satellites and CubeSats over long periods of deployment remains a real stumbling block both for the deployment of large satellite systems and for further exploration of deep space using a new generation of spacecraft. The last few years have seen tremendous global efforts to develop various miniaturized space thrusters, with great success stories. Yet, there are critical challenges that still face the space technology. These have been outlined at an inaugural International Workshop on Micropropulsion and Cubesats, MPCS-2017, a joint effort between Plasma Sources and Application Centre/Space Propulsion Centre (Singapore) and the Micropropulsion and Nanotechnology Lab, the G. Washington University (USA) devoted to miniaturized space propulsion systems, and hosted by CNR-Nanotec—P.Las.M.I. lab in Bari, Italy. This focused review aims to highlight the most promising developments reported at MPCS-2017 by leading world-reputed experts in miniaturized space propulsion systems. Recent advances in several major types of small thrusters including Hall thrusters, ion engines, helicon, and vacuum arc devices are presented, and trends and perspectives are outlined.

Empirical electron cross-field mobility in a Hall effect thruster

Electron transport across the magnetic field in Hall effect thrusters is still an open question. Models have so far assumed 1∕B2 or 1∕B scaling laws for the “anomalous” electron mobility, adjusted to reproduce the integrated performance parameters of the thruster. We show that models based on such mobility laws predict very different ion velocity distribution functions (IVDF) than measured by laser induced fluorescence (LIF). A fixed spatial mobility profile, obtained by analysis of improved LIF measurements, leads to much better model predictions of thruster performance and IVDF than 1∕B2 or 1∕B mobility laws for discharge voltages in the 500–700V range.

Modelling of a dipolar microwave plasma sustained by electron cyclotron resonance

Multi-dipolar plasmas are sustained in large-volume chambers by a network of antennas located at the wall. Each antenna consists of a permanent magnet, trapping electrons in an axisymmetric dipole field, and a microwave applicator, heating the trapped electrons by cyclotron resonance (ECR). This paper presents a two-dimensional self-consistent model of a plasma sustained by one such antenna. The microwave fields and power absorption are calculated from the Maxwell equations coupled with a local electron momentum equation by an adaptation of the finite difference time domain method. The plasma is described by fluid equations for magnetized electrons and inertial ions, where quasi-neutrality is imposed through a semi-implicit numerical method based on Poissons equation, which also yields the sheath potentials. Steady-state model results for argon show that below the critical plasma density (7.4×1016 m−3) the microwave power is absorbed in a narrow region all along the ECR surface around the end of the antenna; beyond this density the main absorption occurs near the plasma edge. Although the electron temperature varies considerably across the magnetic field lines, the plasma potential is nearly uniform all around the antenna and is controlled by the maximum electron temperature.

Chemical composition of SF6 low-pressure plasma in magnetic field

The chemical composition of a low-pressure SF6 plasma in a homogeneous magnetic field is studied using a one-dimensional fluid model. This model takes into account the magnetization of electrons and light negative ions F−. The influence of different parameters such as gas pressure, heating power and magnetic field strength is studied within a parameter range of interest for negative ion sources. The scheme of plasma chemical reactions is analysed in order to identify the main reactions responsible for the generation and decay of plasma species. This sensitivity analysis shows that the scheme of reactions can be significantly simplified.

A comprehensive study on the atom flow in the cross-field discharge of a Hall thruster

The flow properties of Xe atoms were investigated in the 1kW class PPS100-ML Hall effect thruster by means of Doppler-shifted laser-induced fluorescence spectroscopy in the near infrared. Fluorescence spectra of the 6s[1/2] o resonant level and the 6s[3/2] o metastable level have been acquired inside and outside the thruster channel under several operating conditions. Analytical treatment and modelling of the measured lineshapes indicate the atom axial velocity increases inside the channel to a value well above the sound speed before decreasing quickly in the near-field plume. Numerical simulations performed with a fluid/kinetic hybrid approach allow us to explain the shape of the velocity profile. Atomic flow acceleration originates in the combination of three processes, namely the selective ionization of slow atoms, the flow expansion and the creation of fast neutrals on BN-SiO2 walls owing to recombination of ions. Deceleration results from the invasion of the atomic jet by slow and relatively cold atoms from the residual background gas and from the cathode. In addition, it is shown that charge-exchange collisions have a non-negligible impact on the atom velocity in spite of the low background pressure in test chambers. (Some figures in this article are in colour only in the electronic version)

Modeling of an advanced concept of a double stage Hall effect thruster

We present a study of the principle and operation of a two-stage Hall effect thruster, the SPT-MAG, using a two-dimensional quasineutral hybrid model coupled with a Monte Carlo simulation of electron transport. The purpose of the two-stage design is the separation of ion production and acceleration in two separate chambers, the ionization stage and the acceleration stage, with separate control of acceleration voltage and total ionization. The originality of the SPT-MAG lies in the magnetic field configuration in the ionization chamber. Electrons are confined by this magnetic field while ions are supposed to be trapped in the electric potential well supposedly resulting from the magnetic configuration, and guided toward the acceleration stage. The acceleration stage is similar to the channel of a conventional Hall effect thruster. The purpose of this paper is to clarify the physics of the SPT-MAG and to understand the formation of the positive ion trap in the ionization chamber. Using a hybrid model and a ...

Computed versus measured ion velocity distribution functions in a Hall effect thruster

We compare time-averaged and time-varying measured and computed ion velocity distribution functions in a Hall effect thruster for typical operating conditions. The ion properties are measured by means of laser induced fluorescence spectroscopy. Simulations of the plasma properties are performed with a two-dimensional hybrid model. In the electron fluid description of the hybrid model, the anomalous transport responsible for the electron diffusion across the magnetic field barrier is deduced from the experimental profile of the time-averaged electric field. The use of a steady state anomalous mobility profile allows the hybrid model to capture some properties like the time-averaged ion mean velocity. Yet, the model fails at reproducing the time evolution of the ion velocity. This fact reveals a complex underlying physics that necessitates to account for the electron dynamics over a short time-scale. This study also shows the necessity for electron temperature measurements. Moreover, the strength of the self-magnetic field due to the rotating Hall current is found negligible.

Method to obtain the electric field and the ionization frequency from laser induced fluorescence measurements

Laser induced fluorescence (LIF) diagnostic provides a means to measure an ion velocity distribution function (VDF) by Doppler effect with excellent resolution in velocity. This diagnostic has a wide range of applications in low pressure plasma physics and has been used for the past twenty years to study many plasma sources. Most commonly, authors only deduce from the LIF measurements mean ion velocities or accelerating potentials from these mean velocities. However, LIF provides at each measurement position a full VDF which contains much more information than the average velocity. We propose in this paper a new method capable of evaluating the spatial profiles of electric field and ionization frequency. This method consists of establishing a relationship between these quantities and the moments of the measured VDF. We first validate the method by means of numerical simulations and then apply it to two different plasmas: an ICP argon reactor and a Hall effect thruster.

Modeling of double stage Hall effect thruster

Hall effect thrusters (HETs) are ion sources used for satellite station keeping and orbit raising. In Single Stage HETs, the same electric field is responsible for electron heating and ion acceleration. We present a new HET concept where ionization and acceleration are separated in two different stages. This double stage HET allows for a more versatile operation and a separate control of thrust and specific impulse.

Issues in the understanding of negative ion extraction for fusion

A number of recent papers have been devoted to the modeling of negative ion extraction using particle simulations but the published results are not entirely satisfactory and not fully consistent with experiments. Issues raised by the simulations concern the saturation of the negative ion current emitted from the caesiated plasma grid surface, its distribution along the surface, the shape of the meniscus formed around each grid aperture, the distribution and depth of the potential in the virtual cathode, and the profile of the extracted beamlet. These are important issues since they have direct impact on the properties of the extracted negative ion beam (intensity, brightness, aberration). In this paper we first summarize recently published model results that are unexpected and counter-intuitive since they predict that negative ions are extracted from regions of the grid that are directly exposed to the large extraction voltage (i.e. as in vacuum and without the need for a neutralizing background plasma). We then illustrate, with results from two-dimensional particle-in-cell Monte Carlo collision simulations, some regimes of negative ion extraction that are more consistent with the expected physics.